experimental aerodynamic characteristics of missiles with square cross sections

USAFA- TN-863-S

Department of AeronauticsDean of the FacultyUnited States Air Force AcademyColorado Springs, Colorado 80840

tý* EXPERMENTAL AERODYNAMIC CHARACTERISTICSN OF MISSILES WITH SQUARE CROSS SECTIONS

TECHNICAL NOTEUSAFA-TN-83-8

UNITED STATES AIR FORCE ACADEMY

Zollars, G. J.

Vochout, T. R.

UNITED8STATES AIR FORCEARMAMENT LABORATORY .

Daniel, D. C. 0

c.. Lljewski, L. E.

S15 MAY 1983

SAPPROVED FOR PUBLIC RELEASE: DISTRIBUTION UNLIMITED

13 09 '3 126

Any views expressed in this paper are those of the author. They

-. should not be interpreted as reflecting the views of the USAFA•ademy or the official opinion of any governmental agency. .Notes are not reviewed for content or quality by the USAF Academybut are published primarily as a service to the faculty to facili-tate internal research communication.

This Technical Note has been cleared for open publication and/orpublic release by the appropriate Office of Information in accord-ance with AFR 190-17 and DODD 5230.9. There is no objection to

unlimited distribution of this Technical Note to the public at '

large or by DDC to the National Technical Information Service. .'

This Technical Note is approved for publication.

ANN, Lt Colonel, USAFDirector of Research and Continuing Education

AooostO.on For :

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ACKNOWLEDGEMENTS

THE AUTHORS WISH TO EXPRESS THEIR APPRECIATION TO APPROXIMATELY 30 US AIR FORCE

"ACADEMY CADETS FOR THEIR ASSISTANCE IN OBTAINING, RECORDING, AND ANALYZING MUCH OF

THE DATA IN THIS REPORT. IN ADDITION, WE ARE INDEBTED TO OUR COLLEAGUE MAJ. THOMAS

BOLICK WHO PROVIDED THE SOFTWARE SUPPORTAND THE US AIR FORCE ACADEMY AERO LABORATORY

TECHNICIANS WHO PROVIDED THE TECHNICAL SUPPORT.

FORWARD

"A SERIES OF QUANTITATIVE AND QUALITATIVE TESTS WERE CONDUCTED TO EXPAND THE AERO-N •

LfINAMIC DATA BASE OF SQUARE CROSS-SECTION MISSILES. QUANTITATIVE TESTS INCLUDED

MEASURING FORCES AND MOMENTS ACTING ON SQUARE MISSILES, AND MEASURING FLOWFIELD

PRESSURES ON THE LEEWARD SIDE OF SQUARE MISSILES AT VARIOUS CONFIGURATIONS AND OR-

"IENTATIONS IN A SUBSONIC WIND TUNNEL. FORCE AND MOMENT DATA IS PRESENTED SHOWING

THE EFFECTS OF VARIATION IN BODY CORNER RADIUS, NOSE AND FIN SHAPES, PITCH ANGLE,

SAND ROLL ANGLE. FLOWFIELD PRESSURE AND CROSSFLOW VELOCITY DATA ARE PRESENTED FOR

MISSILES OF VARIOUS PITCH ANGLES, ROLL ANGLES, BODY CORNER RADII, AND FINENESS RATIOS

(LENGTH TO WIDTH RATIO). IN ADDITION, FLOWFIELD DATA IS SHOWN ALONG THE AXIAL LENGTH

OF A SQUARE MISSILE.

QUALITATIVE TESTS INCLUDED PHOTOGRAPHING TUFT GRIDS IN THE FLOWFIELD AND PHOTO-

GRAPHING OIL SHEAR STRESS PATTERNS ON THE SURFACE OF VARIOUS MISSILES. THESE

QUALITATIVE PHOTOGRAPHS ARE PRESENTED FOR VARIOUS MISSILE CONFIGURATIONS AND ORIEN-

TATIONS.2'C

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TABLE OF CONTENTS

PAGE

INTRODUCTION 1

DESCRIPTION OF EXPERIMENT 3

TEST RESULTS 8

REFERENCES 17

APPENDIX A - FORCE AND MOMENTCOMPARISONS OF VARIOUS MISSILE

CONF I GURAT IONS 19

APPENDIX B - TABULAR LISTING OF

FORCE AND MOMENT COEFFICIENTS 54

APPENDIX C - QUANTITATIVE FLOWFIELD

MEASUREMENTS 125

APPENDIX D - TUFT GRID PHOTOGRAPHS

OF THE FLOWFIELD 165

* APPENDIX E - OIL FLOW PATTERNS 201

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ILLUSTRATIONS

FIGURES PAGES

1" WIND TUNNEL SCHEMATIC 10

2. COMPONENTS OF MISSILE WITH

FINENESS RATIO 7,5 11

"3, MODEL COMPONENTS 12

4. ASSEMBLED MODEL OF SQUARE

MISSILE 13

5. MISSILE OF FINENESS RATIO 16COMPONENTS 14

6. DIRECTION OF POSITIVE FORCES 15

7, SEVEN-HOLE PROBE AND

POSITIONING SYSTEM 16

A.1-A,18 BODY AXIS FORCE AND MOMENTGRAPHICAL COMPARISONS 24-41

0 A,19-A,30 WIND AXIS FORCE AND MOMENT"GRAPHICAL COMPARISONS 42-53

B.1-B,40 TABULAR PRINTOUTS OF BODY AXIS

FORCE AND MOMENT DATA 59-98

"B.41-B.66 TABULAR PRINTOUTS OF WIND AXIS

"FORCE AND MOMENT DATA 99-124

C.01 FLOWFIELD MEASUREMENT PLANES--

AXIAL VIEW 129

. C.02 DATA MEASUREMENT PLANES--CROSS-FLOW VIEW 130

C,1-C.13 VELOCITY VECTOR AND PRESSURE

CONTOUR FLOWFIELD PROFILES

*; FOR MISSILES OF FINENESS

RATIO 8 133-158

C.14-C.16 VELOCITY VECTOR AND PRESSURE

CONTOUR FLOWFIELD PROFILES

b .FOR MISSILES OF FINENESSRATIO 16 159-164

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ILLUSTRATIONS

FIGURES PAGES

D,01 SIDEVIEW OF TUFT GRID TESTSETUP 167

D.1-D,23 TUFT GRID PHOTOS FOR MISSILESOF FINENESS RATIO 8 171-193

D,24-D,30 TUFT GRID PHOTOS FOR MISSILESOF FINENESS RATIO 16 194-200

E.01 POSITIONS OF MISSILE DURINGWIND TUNNEL EXPERIMENT ANDPHOTOGRAPHY 203

E,1-E.35 OIL FLOW PHOTOS FOR MISSILESOF FINENESS RATIO 8 207-241

E.36-E.41 OIL FLOW PHOTOS FOR MISSILESOF FINENESS RATIO 16 242-247

(IV

(Iv)

TABLES

TABLE MEA-i NOMENCLATURE OF FORCE AND MOMENT

COEFFICIENTS 21

A-2 SUMMARY OF FORCE AND MOMENT GRAPHS OFBODY AXIS AND WIND AXIS DATA 22-23

B-i NOMENCLATURE OF FORCE AND MOMENTCOEFFICIENTS 55

B-2 SUMMARY OF FORCE AND MOMENT TESTS (DATAPRESENTED IN BODY-AXIS FORMAT 56-57

B-3 SUMMARY OF FORCE AND MOMENT TESTS (DATAPRESENTED IN WIND-AXIS FORMAT) 58

C-1 SUMMARY OF QUANTITATIVE FLOWFIELD TESTSFOR MISSILES OF FINENESS RATIO 8 131

C-2 SUMMARY OF QUANTITATIVE FLOWFIELD TESTSFOR MISSILES OF FINENESS RATIO 16 132

D-1 SUMMARY OF TUFT GRID PHOTOS FOR MISSILESOF FINENESS RATIO 8 168-169

D-2 SUMMARY OF TUFT GRID PHOTOS FOR MISSILESOF FINENESS RATIO 16 170

E-1 SUMMARY OF OIL FLOW PHOTOS FOR MISSILESOF FINENESS RATIO 8 204-205

E-2 SUMMARY OF OIL FLOW PHOTOS FOR MISSILESOF FINENESS RATIO 16 206

(v) L

'I

"INTRODUCTION

During the last several years there has been increasing interest

in rectangular or square cross-section bodies for missiles and

submunitLon applications. This interest is due primarily to the

"increased packing efficiency that results from the rectangular

shape as compared to missiles with circular cross sections. This

packing efficiency gain is due to two factors: (1) the ease of

packing rectangular modular components and (2) greater usable

volume for a given frontal area. What must be determined, how-

* ever, is whether this well-recognized packing advantage is out-

weighed by possible detrimental aerodynamic effects.

, . Unfortunately, only a limited amount of aerodynamic information

exists which could support preliminary design or analyses of mis-

silea with square cross-sections, especially those requiring

moderate amounts of maneuverability. These limited studiesinclude the two-dimensional work by Polhamus (Ref. I and 2) which

investigated with the aerodynamic characteristics of several

non-circular 2-D cylinders with the longitudinal axis normal to

the freestream flow. Drag, side-force and pressure coefficient

"variation with Reynolds number was investigated with a primary

stability predictions for fuselages at high angles of attack.

Additional work was conducted by Clarkson (Ref. 3) on a rectangu-

lar cross-section forebody at an angle of attack between 45 and

90 degrees. This work concentrated on investigating side-force

and pressure coefficient variation with Reynolds number and the

reasons for the failure of simple cross-flow theory to predict

N behavior at high angles of attack. Finally, Knoche (Ref. 4) and

Schneider (Ref. 5) briefly investigated the aerodynamic charac-

teristics of bodies with rectangular cross sections. In general,

however, there is little in the technology base to support design

of three dimensional applications.

To assist in overcoming this deficiency, the Air Force Armament

Laboratory and the Air Force Academy conducted a research program

to analyze the aerodynamic characteristics of missiles having*•4

square cross-sections. The first phase of the program was con-

corned with measuring the experimental forces and moments on

square missiles for a wide range of geometries, orientations, and

flow conditions. Photographic documentation of surface oil-flow

patterns which define the shear stress distribution along the

missile surface were also recorded. The second phase of the pro-

gram was concerned with detailed flow-field measurements. Pres-

sure measurements were recorded in various planes of the flow-

field and pressure contours were mapped of the flowfield. In

addition, tuft grid photographs were taken to describe the flow-

field. This report presents results from each of the two phases

of the research program which began in November 1979 and extended

through December 1982.

2

II DESCRIPTION OF EXPERIMENT

All testing was conducted at the Air Force Academy Aeronautics

Laboratory using the subsonic wind tunnel. Easically, two types

of quantitative tests were conducted: force and moment measure-

ments and flowfield pressure measurements. The force and moment

measurements were made using an internally mounted steady state

strain gage balance in a free stream velocity of 360 ft/s and

atmospheric pressure. The flowfield measurements were made using

a 7-hole pressure probe mounted on a three-directional traverse

mechanism. This data was taken at a free stream velocity of 100

ft/s and atmospheric pressure. in addition, two types of qualita-

tive tests were conducted: tests to record oil flow patterns on

the surface of various shaped missiles, and tests using a tuft

grid matrix to record cross-flow velocity patterns on the leeward

side of the missile. Oil surface tests were conducted at 360

ft/s, and the tuft grid tests were conducted at 100 ft/sec.

1. Wind Tunnel (Ref. 6)

The U.S. Air Force Academy subsonic wind tunnel is a continuous

flow closed circuit facility which has a test section of two feet

by three feet and is capable of operation between Mach numbers of

0.04 and 0.35 at atmospheric pressure. At the maximum operating

condition, the tunnel is capable of operation at a unit Reynolds

9 3

number of 1.6 million per foot. The nominal turbulence level of

the test section has been measured at 0.12% based upon an overall

spacial average for a velocity range of 60 to 150 fps. A general

schematic is presented in Figure 1.

2. Wind Tunnel Models

Two sets of models were tested in the experiment: one set with

%: fineness ratio equal to 8 (fineness ratio is defined as the

length to width ratio of the missile), and another set with fine-

ness ratio equal to 16. A description of each set of models fol-

lows.

A. Models of Fineness Ratio 8

The various model components used in this investigation are shown

in Figures 2 and 3. These figures depict the four bodies, each

with a different cross-section corner radiusy the two noses, a

blunt-tangent ogive, and pointed-tangent ogive, and one each of

the three sets of fins that were used. All components were made

of aluminum. As illustrated by the figure, the four body cross-

sections ranged from square (Bl) to round (B4) and were defined

by a normalized body corner radius ratio (r/b) r being the radius

of the corners and b being the diameter of the circular missile.

The values investigated were 0.0, 0.1, 0.2, and 0.5. These

Ii k..4

bodies are depicted in Figures 2 and 3 as I, II, III, and IV

respectively. Each body section was 12 inches long and had a

width (diameter) of 2 inches. The blunt tangent ogive nose (Ni)

shown in Figure 2 was 3 inches in length and had a bluntness of

0.69. The pointed-tangent ogive nose (N2) was 4 inches long.

The three sets of fins were designated Fl, F2, and F3, and had

aspect ratios (based on exposed semi-span) of 0.47, 0.67, and

0.34 respectively. Fins F1 and F3 had an exposed semi-span of

1.25 inches and lengths of 4 inches and 6 inches respectively.

Fin F2 had an exposed semi-span of 1.5 inches and a length of 3

inches. The four bodies, two noses, and three sets of fins were

used to make various configurations of the missile model. An

assembled model, is shown in Figure 4. As can be seen from this

5 figure, the fins are mounted in a standard cruciform arrangement

at the corners of the body.

B. Models of Fineness Ratio 16

The model components of the missiles of fineness ratio 16 are

shown in Figure 5. This figure deposits five bodies, each with a

different cross-section corner radius, and two noses, a blunt-

tangent ogive and a pointed-tangent ogive. These components were

also made of aluminum. Fins were not used on these high fineness

ratio missiles. As illustrated in the figure, five bodies were

tested and ranged from perfectly square (designated missile 1) to

• ," ,5

perfectly round (designated missile 5). The normalized body

corner radii (r/b) values of these five bodies were 0.0, 0.1,

0.2, 0.3, and 0.5. The bodies are depicted in Figure 5 as 1, 2,

3, 4, and 5, respectively. Each of these bodies were 20 inches

long and had a width of approximately 1.5 inches. The two noses,

the blunt tangent ogive and the pointed tangent ogive, were 3"

* and 4" in length, respectively.

3. Force and Moment Balance

A .75 inch diameter, steady state, internally mounted strain

gauge balance was used to measure the force and moment components

on the square-shaped missile bodies in three axes. The balance

*[ is capabla of measuring forces to an accuracy of 0.1 percent.

Forces and moments were recorded in either the body or wind axis

systems with the axis origin at the balance center. Figure 6

illustrates positive loads recorded by the balance and the posi-

.! tive force directions in the body and the wind axis systems with

respect to the square missile.

4. Flowfield Test Measurement Apparatus

*: A seven hole pressure probe developed at the United States Air

Force Academy was used to measure pressures on the leeward side

of various missile configurations (Ref 7). The Seven-hole probe

-" ~6

is capable of recording total pressure, static pressure, and

S -fluid velocity in all three axes and has been calibrated for

incompressible fluid flows up to 80 degrees, measured from the

flow directions to the probe axis. Figure 7 depicts the seven-hole probe used in the experiment. As shown in the figure the

probe is approximately 0.1 inch in diameter. To position the

probe on the leeward side of the missile body, a three-

directional traverse mechanism was used. For all flow field

measurements taken, the traverse mechanism was used and was posi-

tioned to place the probe in a plane behind the model. Figure 7

shows the traverse mechanism.

5. Data Acquisition and Processing

All data was acquired using an Automated Data Acquisition System

and a PDP 1145 computer. Raw data from either the strain gagebalance or the seven-hole pressure probe were input into compu-

terized data reduction programs which computed the force and

moment coefficients illustrated in Appendix A or total pressures

and velocity cross flows illustrated in Appendix C. Graphical

plots were obtained using the PDP 1145 computer and a Tektronix

4662 Interactive Digital Plotter.

7

6. Qualitative Tests Apparatus

To enhance our understanding of the flow field pressure and velo-

city patterns obtained by the pressure probe, tuft grid tests and

oil flow tests were also conducted. Tuft grid tests were con-

ducted by placing a grid of wool tufts in the flow field and then

photographing the tuft patterns. Appendix D shows the tuft grid

photographs. Oil flow tests were conducted by painting the

models black and then spraying white oil in a light speckled pat-

tern on the models. The oil was a mixture of titanium dioxade,

oleoic acid and 90 weight transmission oil. After the tunnel was

brought up to the appropriate speed and the oil migrated suffi-

ciently over the surface of the models to define the shear stress

distribution, photographs were taken of the oil flow patterns.

Appendix a shows the photographs of various oil flow patterns.

III TEST RESULTS

Results of the tests performed are illustrated in Appendices A

through E. A short description of each test is presented at the

beginning of each Appendix. Analysis of the data is left for the

reader, although several papers (Ref. 8-10) have been published

which analyze various aspects of the data. A description of the

test data presented in each appendix is described below.

8

.Appendix D ition of Tests Results

A Force and Moment Graphical comparisons

of various missile configurations. Data

is presented in either the body or wind

axes format.

B Tabular print-outs of Forces and Moments

measured on various missile configurations.

Data is presented in either the body or wind

axes format.

C Quantitative flowfield data. Data includes

both plots of total pressure contours and

cross-flow velocity vectors in a plane of

the flow on the leeward side of the missile.

Plane of data is perpendicular to the free

stream velocity.

D Photographs of tuft grid patterns describing

the flow field on the leeward side of the missile.

E Photographs of oil flow patterns on thi surface

of missiles tested in various configurations.

4.

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AFT NORMAL FORCE

POLLING: ~MOMENT -

FORWARD NORMAL FORCE AFT SIEr•'• • .,FORCE

,,,. FOWARD SIDE FORCGE

!"'• LOZW " (AXIAL,) FORCE#

Figure 6a. Balance Loads

0 O y -c

ZERO DEGREES ROLL "y ZERO DEGREES ROLL

0 DEGREES ROLL 0 DEGREES ROLL

SBODY AXIS FORCES WIND AXIS FORCES

Figure 6h. Body and Wind Axis Systems (Looking at Aft Side ofthe Model). Direction of Airflow Is Out of Plane ofPaper

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Figure 6. Direction of Positive Forces

15

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4 Figure 7. Seven-Hole Probe and Positioning System

16

References

I. Polhamus, E. C., Geller, E. W., and Grunwald, K. J., "Pres-

sure and Force Characteristics of Noncircular Cylinders as

Affected by Reynolds Number with a Method Included for Determin-

ing the Potential Flow About Arbitrary Shapes", NASA TR R-46,

1959.

P'

2. Polhamus, a. C., "Effeet of Flow Incidence and Reynolds A

Number on Low-Speed Aerodynamic Characteristics of Several Non-

circular Cylinders with Applications to Directional Stability and

Spinning", NASA TR R-29, 1959. :1S3. ClarksonAM. H., Malcolm, 0. N., and Chapman, G. T., "A Sub-

sonic, High Angle of Attack Flow Investigation at Several Ray-

nolds Numbers", AZAA Journal, Vol 16, No. 1, January 1978, pp

53-60.

4. Knoche, H. G., Schamel, W., "Aerodynamic Characteristics of

Bodies with Rectangular Cross Section", AIAA Aerospace Sciences

Meeting, January 1981, Paper No. 81-0145.

5. Schneider, W., "Experimental investigation of Bodies with

Non-Circular Cross Section in Compressible Flow", AGARD CPP 336,

Missile Aerodynamics, September 1982, pp. 19-1 - 19-11.

i

17

6. "Subsonic and Trisonic Wind Tunnel Facilities", Department of

Aeronautics, U. S. Air Force Academy.

7. Gerner, A., Sisson, G. "Seven-Hole Probe Data Acquisition

System", USAPA-TN- 81-8, 18 Nov 1981.

8. Daniel, D. C., Yeohout, T. R. and Zollars, G. J., "Experimen-

tal Aerodynamic Characteristics of Missiles with Square Cross

Sections", Journal of Spacecraft and Rockets, Vol. 19, No. 2,

March-April 1982, pp. 167-172.

9. Daniel, D. C., Lijewkil, L. R. and Zollars, G. J., "Uxperi-

mental Aerodynamic Studies of Missiles with Square Cross Seo-

tions", AGARD CPP 366, Missile Aerodynamics, September 1982, pp.

18-1 - 18-15.

10. Lijewski, L. E., Zollars, G. J., Yechout, T. R., Haupt, B.

F., "Experimental Flowfield Measurements of Missiles with Square'I

Cross Sections". AIAA Aerospace Sciences Meeting, January 1982,

Paper No. 82-0055.

"441'8

-II

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Appendix A

FORCE AND MOMENT COMPARISONS OF VARIOUS MISSILE CONFIGURATIONS

Force and moment tests were conducted only on the missiles of

fineness ratio equal to 8. Each model configuration was mounted

on the sting at the pitch center of the pitch rotation system

which placed the force and moment balance center at the tunnel

"test section centerline. Six components of force and moment data

were taken in two degree increments from 0 to 30 degrees pitch

angle at roll orientations of 0, 11.25, 22.5, 33.75, and 45

degrees. The angle between the longitudinal axis of the sting

and the freestream velocity was defined as the pitch angle and

for a 0 degree roll orientation the pitch angle and angle of

attack were the same. At the other roll orientations the pitch

angle equated to a combination of angle of attack and sideslip.

The freestream velocity was approximately 360 fps (M * .31) and

the Reynolds number was approximately 2.5 x 105 for all tests.

Forces and moments were recorded in either the body or wind axes

systems. All results were non-dimensionalized using the cross-

sectional area (0.0218 square feet) of the circular body (IV) and

a length of the body cross-section width (2 inches for bodies I-

IV).

P4Force and Moment coefficients are graphically plotted in Figures

A-01 through A-30. Figures A-01 through A-18 show body axis data

19-Ij

while Figures A-19 through A-30 show wind axis data. All coeffi-

cients are plotted versus pitch angle from zero to 30 degrees.

Besides showing the effects of pitch angle variation, the graphs

"also illustrate the effects of changes in body corner radius,

nose variation and fin variation. Also shown above each graph is

a data scheme that illustrates the missile configuration tested.

Each configuration was labeled according to the component nomen-

clature shown in Figure 2. For instance, the square body tested

at 22.5 roll and with the 4-inch length fin and blunt nose con-

figuration is noted as 1/22.5/FI/BL. Table A-i illustrates the

nomenclature for the force and moment coefficients. Table A-2

summarizes the 30 figures in the appendix.

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TABLE A-i"FORCE/MOMENT COEFFICI ENTS

5 Wind Axis Body Axis

CL - Lift Coefficient CN - Normal Force Coefficient

CD - Drag Coefficient CA - Axial Force Coefficient

CC - Cross-Force Coefficient CY - Side-Force Coefficient

SMW - Pitching Moment Coefficient CM - Pitching Moment Coefficient

CLW - Rolling Moment Coefficient ROLCO - Rolling Moment Coefficient

CNW - Yawing Moment Coefficient YMCO - Yawing Moment Coefficient

Ii I,4 .|

:', 21

'" ' ' " ." 1 " ' . . . " • . ". . . . ' " " " " . . -- ' . , .. • "-' '-" -- • , "

TABLE A- 2

SU4MARY OF FORCE AND MCMOIT GRAPHS -

BODY AXIS SYSTEM DATA

Appendix Missile ParameterFiurOe Confi&Lration Varied

A-i dO Roll, No Fins, Blunt Nose Corner Radius (Bodies I-IV)

A-2 220 Roll, No Fins, Blunt Nose Corner Radius (Bodies I-IV)


A-4 O4 Roll, Fin s, Blunt Nose Corner Radius (Bodies I-IV)

A-5 220 Roll, Fin 1, Blunt Nose Corner Radius (Bodies I-IV)

A-5 220 Roll, Fin 1, Blunt Nose Corner Radius (Bodies I-tV)A-6 450 Roll, Fin 1, Blunt Nose Corner Radius (Bodies I-IV)

A-7 Missile III, 00 Roll, No Fins/Fin 1 Noses (BL & PT Noses)

A-8 Missile III, 220 Roll, No Fins/Fin I Noses (BL & PT Noses)

A-9 Missile 111, 45 Roll, No Fins/Fin I Noses (BL & PT Noses)

A-i1 Missile III, 00 Roll, F1 & F3 Noses (BL & PT Noses)

A-11 Missile 11, 220 Roll, F1 & F3 Noses (BL & PT Noses)

A-12 Missile 11, 450 Roll, Fl & F3 Noses (BL & PT Noses)

A-13 Missile III, 00 Roll, Blunt Nose Fins (NF, F1, F2, F3)

A-14 Missile 111, 22" Roll, Blunt Nose Fins (NF, F1, F2, F3)

0A-15 Missile III, 45 Roll, Blunt Nose Fins (NF, F1, F2, F3)

A-16 Missile III, 0o Roll, Pointed Nose Fins (NF, F1, F2, F3)

A-17 Missile I1, 220 Roll, Pointed Nose Fins (NF, F1, F2, F3)

A-18 Missile 111, 450 Roll, Pointed Nose Fins (NF, F1, F2, F3)

2

.22

.. . . . . . . . ,. ' " "• ' . . . . . I . ..: .... ... ...... i... ........ A, .. A . 4. * - . . ........ I... ........ .. ...... .... *... .....- i .. .. .. . ..-i " " . .."

Table A-2 Summary of Force and Moment Graphs (cont'd)

WIND AXIS SYSTEM DATA

Appendix Missile ParameterFiaure Confixuration Varied


A-20 330 Roll, No Fins, Blunt Nose Corner Radius (Bodies I-IV)ABoA-21 110 Roll, Fin 1, Blunt Nose Corner Radius (Bodies I-IV)

00A-23 Missile 331, 11 Roll, No Fins/Fin 1 Noses (BL & PT Noses)

A-23 Missile III, 1°0 Roll, No Fins/Fin 1 Noses (BL & PT Noses)A-24 Missile I11, 330 Roll, No Fins/Fin 1 Noses (BL & PT Noses)

A-25 Missile III, 110 Roll, Fl & F3 Noses (BL & PT Noses)

A-26 Missile 111, 330 Roll, Fl & F3 Noses (BL & PT Noses)-R0

A-27 Missile III, 113 Roll, Blunt Nose Fins (NF, Flo F2, F3)

A-28 Missile 111, 330 Roll, Blont Nose Fins (NF, Fl, F2, F3)

A-29 Missile III, 110 Roll, Pointed Nose Fins (NF, Fl, F2, F3)

A-30 Missile 111, 33 0Roll, Pointed Nose Fins (NP, Fl, F2, F3)

'-'" 23

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.i,,. - ,

..,, -,o - - a" ,esel -• • .... .

"* -lle1.0 oU I5 4 14.0W 1 Al.. NoL 11.006 31.0W 331., -|,i-

FIGURE A-1. BODY CORNER RADIUS EFrECTS ,r

FIGURE A-1.4 BODY CORNER RADIUS KFFECtS-- i 6O,'HP'D0 ,L

aIU,,l.1NPe,,l. ...- ,,lll..-h -~B1W1 -- jIU'I. I•,,'L

*41I G,0.........................

L '

,-,an

-0.,001-- ,- -. . . . . . . . . . . . . . . . . . . .. .... . . ..

FIGURE A.-t.2 BODY CORNER RADIUS EFFECTSLL

.. •.,,. o~. ,,,,,ol..... ...... ........... ...o.. .o.., -o.o .$.off ....... 0.5. -,,0.,o oo ,oo ,0;,.:

•rFIURE A-I,5 BODY CORNE•R RADIUS EFFEICTS

•. ......" ' HP.I. .It..-HH- -I-,-,- -,,,I.

0, ...... . . .... . ..-.

-M. "S-. 604 8.6 .m 0.. i s ...... . Ise ....... w""s.

-0, a..O,# . ..

-,,,, , ,, - - ,, ,,,, - ~ o,, ,- ,,,o e.-,o - ,. , .,,o.o ,-., .

FIGURK A-1.3 BODY CORNER IlADIUS IFFICTS FICUPS A-1.6 BODY CORNER RADIUS EFFECTS

FIGURE A-1. BODY AXIS FORCE & MOMENT BODY EFFECTS, 0 ROLL ANGLE.

NO FINS, BLUNT NOSE.

24

.............................. S. A. . .,...*

-.... fi I 'w.I ,'O • - 39'3$* ,i

Uolew'ol.9 h,11,35

4. 0"

.,' I, ,, ..

- -,-.... -

alue " ' • -" IWM +-o -" - -Pc-

.9MIS

4.W -Is-m isema tooW -s cm cm tou ikg -o n.M0 34.00.3S.

FIGURE A-2.1 BODY CORNER RADIUS EFFECTS FIGURE A-2.4 BODY CORNER RADIUS IFFECTS--''.:.: , , ,",1 .. -'

c -$-,--e-e -

I4~c

-I,

0.6. .- -

v,, -,. . -- L--i

&, 4.5--,- -,9

I94 -, -L + ,

4.W-.

9.99

"~o" .4h0,I 0

" P%~FGURE A-1P,3 BODY CORNER• RAD)IUS EFrFECTS F'IGURE A-2.6 SIOUY CORNE•IR RADIUS |'EFFECTS ',9 *

2 5

-,

-gm,,m g.m m aes~ a m 3.5 1 -g. g m gm g mImW¶~Oe ~ Sw.. RE - -. BOD CONR A:,"FECSFIJRE A . .LY.ON.,ALU4 EFE

PTGURI A- I GUBO Y CRE ' RA- . BD Y AIU S FORel C E ME T OD EFFECR T S - 2, 2 R~OL) AONGLE D U.I [rl[ T

.' "+ NO FPINS, BlL UNT NOS E.

+d ~25

- 41 P -., L ..... ,II

4. "s

'sat. ,, - -.. -

1 "1

-N."s ,4 140 S.0 -.9 IsW Ih24B0043 5001 ISM Wt % weIa .1::: I i ,fl•- 111-I- - -,

-. m~e o,me sassl~eei•••~oee~e I oRe.t noS~m os iae m ao~eee11ase.e n~ee;, e m

FIGURE A-3.I SODY CORNER RADIUS EFFECTS FIGUR A-3.4 BODY CORNER RADIUS EFFECTS

So ... . .

""- vi is* w n,

• s,,,,s - '.5.-- -..

-sIo.- . "

-i! saowsoo o noooss 5555so 5 *.assN smoo smoo soass is•s.soo no,5 sos55 15oo.n

PtO I A-3.2 BODY CORNER RADIUS EFFECTS FIGURE A-3.5 BODY CORNER RADIUS EFFECTS

*5 1 -- -,,.,.,,, -_•. a 2 ...- ,.,

-01-0" ~ $IfIITil

17-3.004--.,. 04 S .04 1. 400 te o "LI¶'

5 f.- -,,- s.. -se M oo 1eas s•ass HI..,,s aim 36.60 6 31.

FIGURE A-3J. BODY CORNER RADIL.9 EFFECTS FIGURE A-3.- BODY CORNER RADIUS ZFTE.ITS

FIGURE A-3. BODY AXIS FORCE , MOMINT BODY EFFECTS, 45 ROLL ANGLE.

NO FINS, BLUNT NOSE.

26

- :'oi SL- I4414LSI~e,0FIlL -- IU,4',FSIL110 ..... LO,|O ....... I|' 1 !5 1941.

4.0 .. .- ......

I. ~ ~ ~ , -f S#1

'a.. ---- oso;.,I.---------------------------

-I',0M 0.6,0 140061100 1 tell" IS . ,,, 6.60 0 6 .0546 is .60IM 0 4

HOURh A-4.1 BODY CORNER RADIUIS EFFECTS FIGURE3 A-4.4 BODY CORNER RADIUS AFFECTS

+'~.... + 0,a,.. .40I

I _no :,404.4,1 .sells-

4404O - soo

k0 . _ - M ....-. . ..

j% 040 $"1460 1

FIMURE A-4.2 BODY CORNE RADIUS EFFECTS FIGURE A-4.3 BODY CORNER RADIUS EFFECTS

t* 411I-

-~ll -- , --10 ,'

Y 0.

alt.

-4.041 - - -00a -w

--. 609_ -

-0.60O 0.60 1.000 1.998 11= 16.04 21009 M.00 Is. -1.0" 8.044 .4W 18.00 4R1$3%IO.oo6 250649 30.66 39.

rtGURE A-4&.3 BODY CORNER RADIUS EFFECTS FIGURE A-4.6 moDy CORNER RamIU ErPECT9

FIGURE A-4. BODY AXIS FORCE & MOMENT BODY EFFECTS, 0 ROLL ANGLE.

FIN 1, BLUNT NOSE.

27

-- I-iz.!'Fl'- -- I,'2l,5rl'I',

l.Il III I

cmSm qm e0IMHi m 5 -SI 65.4"s 5 5 5-Ika~sIIm364

." - " I.5li ---

i .4 M .

....... .. ... IF. . -- ., "-

I .I N 4- . 0 6

A *83~-.40-9 1 6-K

-I.1O @e.O 1s.m1 olwO ISjlf.md Mn 36.011. 3s. -1sD O M 9.m66 1 s0mO ,i sqa 16.lli 2.081 3 owis4 3.

FIGURE A-1.) BODY CORNER RADIUS EFFECTS FIGURE A-5.6 BODY CORNER RADIUS EFFECTS

II,,h,,h :i A-5 iBODY AXIS FOC OETBD ,i 2,RL AGE

1'.FN1 1 UI' NOSE.

!.'l. ~I. II.hb - -I.. -.- 2

..-S..-

-O, ill1/I -4,/U.

,ii .,,h!,,i'

'-5*

-4,111 --- - --. % . -

!I QURE 4-¶,J BODY COR• IP RADIUSI EFFlECTS 'IGUUR A-5.6 BODY CORNER RADIUS EFFE*CTS

F'1GU W: A-5, BOD Y, AXIS FO RC E• 4 MO MENT BODY I•F FECT S,S 21 ROLL A•IGL E,

FIN 1, BLU]I4T NOSE.

283

- S .• , .o, • . . . •

1 h4 5 1i-CLi1U145PI'SL IU45'PI4

-1 45,*

IV/43 F1,1 !

S~4L.....0.009

cI

-11.60 6e.60 8.804 e6.0e 30%jaee 041 ISS 36.6416 30. -eee lieee 5.68 11s.0113m M041 1$~~.*0 3ee .0413v.FIGURE A-6.1 BODY CONNEB RADIUS EFFECTS FIGURE A-6.4 BODY CORNER RADIUS EFFECTS

-f45IL 11 1~~' ok

2.~~S 4"I'L

-. mSim

-0.aer6 - 1.404L

!1 -46 000 sR l IM MA" M4 WI35 "1.64M MIS$N*6001 4441.0 601

FIUEA62BODY CORNER RADIUS EFFECTS FmouRs A-6.5 BODY CORNER RADIUS EtFPECTi

j,'44iF1'SL

- eo

-406 2.644 ..................... *

L * .Si -- Aa. 1....... - 4.00- - - - - - - -

v Ns

-3 ofC.Is 0 t o 0LS1,061.643.0 3.-164 668 514 IN lt- 5663.0 5*A *A

r1611K A6.3 ODY ORNE RA IUS 0rt ~ IUEAb6 BD ONRPDU FE

'1(~~RE -~ * OUYCRNER RA-.BDYU AISFOCEs MOMENT BODY EFFCT 45U COLLE M AGM SEFFCT

FIN 1, BLUNT NOSE.

29

0OHF PT HF/ I

-I.i II4a

-Itm 1.m 11.0111 1$.m lk ewoom nm osewa 23. -vim Its soml loml ¶1$4M~.sm #I.$"3mK 1110133

FICURE A-7.1 NOSE EFFECTS FIOURVA-1.4 NOSE EFFECTS

6.301 -1 -

0 4

VIXOURE A-7.2 NOSE EFFECTS FIOURE A-7.5 NOSE IFFECTS

"1'14111 -lessIII.g40i - - - . -- - -

FIGURE A-1, BODY AXIS FORCE & MOMENT NOSE EFFECTS, MISSILE 111,

ROLL 0, NO FIN/FtN 2, BLUNT/POINTE.D NOSE.

30

- - lt~.' 'J ~'Ll~t-2.~ 14F 11.

"". . 11. 1 E

too Isl[e"

35.o -1.08 1.m 1.6 @4@1 t.OtHs 0.0

FLOURS A4.1 NOSE EFFECTS FLOURS A4 .4 NOSS EFIICTS

0.- -- 0ss.

-seessestee s.ee asses0 asse 30,0s 35. -sees4 eweb sew6 Isis$e s.4%, too$$ Hasee asses1 35,

FIGURE A-412 Nost 7FFECTS FIGURE A-6.3 NOSE EFFECTS

* ii L~I*'I'0000. 000 11.00

oI.soo -- - - - - - ee - --- -

-i~e.. - 1.46s

-1490 :I T-~

-4.04

-IUR A--, -8 BODY AXI FORCE -OEN -OS EFECS MISIL III

ROL 22ssr NOINFN2,BUTPIN OE

I 31

1- tlt'45'H.....1vS 1--------------------------------------------- 1 1.48FlPI.

I' 4,~~~~1.900*e;~5,wl~wee

*i m e ewi0.0e sssase t

FIcU toQ. NOE£TEN: Sim - : qN~s

-. 16.00----------------------

FIGURE --. O&ZFCSFCUKA94 HS ET

.4.

AS-1

s~esi~. -. 4.5 5 6

-uses01 ee S m e 5 e0 e 1fsm I s.em 1u.6ezMISSe Us. -Sim e.9e sees 10sses 114s l.$was ass I SoM4 0 3S.FIGURE A-9.23 HOSE MICTS FIGURE A-9.5 NOSE EFFECTS

32 14

-- tII.iO.Pl.L -- tII/lrl.0' ",0S...... . F1 ,O-tI .PT ..... L I,', 0 .~l TSI... .. l P,3'SL ... 1|I'SP3'SL

--- III.'O'F3"PT -- - 1III/g/3-PT

$.ON _. .f

1,11 o o 'r +- - Oe eo-lll- -- -

ON

-, -/-sIOoe---------

-0,441 4.6041 1,,441 11.444 Is%s. o se1,o,,o 6.6o, .,,. , -5,.64 0o,04o,5,**. ,*** MW •. lt os, 15*.08-,.o4,o. ,FIGURE A-10.1 NOSEt errcTS FIPTGURE A-10,4 NOSE EFFECTS-P.

-- ,,,+ +,tll~ ,+EL+Ilt000Ii~~

s1omm lI

"•1 Oil, .. r•............o...,..................

%'IUl% ,ool -

--," m. - ,--8

"1-- .1.04167 - I

rICURL A-10.2 NOSE EFFECTS FIGURE A-1 •.I NOSE EFFECTS

- .1~ , !I' ,I,

1, ::z l, 0e

1.01 1

0

-1..- -. 00k- N -ON...

8..00 - -.- i , L. - ' " .--1 5 8--o,, -1 -- -ior -o-ol- - . - --+- - -

4,00 6,000f 50IS.0 ~ 1 .0 "1~ 31.016 35, -5.04 0.809 5,4004 19.00015W *50 0 6 2 6.0k34e 35. .

-I ~FIGURE A-LO.3 NOSE2 EFFECTS FIGURE A-IC I, NOSE .EHEM

FIGURE A-10, BODY A11S FORCE & MOMENT NOSE' EFFTS, MISSILE III.

ROLL 0, FtIN t/rtN 3. BLIJNT/P'(TN'%V NOSr,

33

-- - I I.; , Vl L II... - I 2-.ý•• • FI ýL .. .... o 315. f T SI.22, I.. F Pt

6.. . .3. L --- - II '2 ,.5 F3 L .- 1.. pr..-- - 1 .-2,5"F3 PT

4.. ,,

FIGURE A-11.1 NOSE EFFECTS FIGURE A-11.4 NOSE EFFECTS

5'13, I5P>L

0,201 ........ M ...... ~* - - o,..,s

' 0 -- -lI --•.+IO -- l!4* ,- IIIC - -P - - IZZb'3.P ]

.40------------------.l

V.6L3

S....... .,,I -F , . -I.. . _

4.000 l.0 . .

-. 081' - -ie--- i

- 2.000--------------------------------------------------------- ll'il/sl---- ll,2ll.p

4 . 00I - -M5. .0 5.000 10.800 15,900 20.00 15.000 30.000 4n010

-,.o+ .-. .-,.,

ALPHA ALPHAFiGURE A-11.3 NOSE EFFECTS FIGUUE A-11.6 NOSE EFFECTS

FIGURE A-11. BODY AXIS FORCE & MOMENT NOSE E.FFECT3, 4ISSILE III.

ROLL 22, FIN W/IN 3, BLMIT/POINED NOSE.

34

r.. 1 K ' I T..... 1l .4' "1S. . . I I4 •F ,L - -.... .l.-,' II rI iIZ145' F 3 i1 -4* i 'S11 .45 F 'Ft --F 7 1 .. IT' I F T

10 , O'ki5 .0 . ..

8 ,000 10,009 _

4l0

+,..,.... 7 17,v . .. ....

- - ,- - - -,--0-- -

4ooH - - -| -~

-5.O0 0.606 5.600 10.000 15.000 20,.0 00 254,O00 30.000 35., -5$.4 * i.s0 5.o00 1s.o00 15.oo0 sOo00 15s000 30.000 34.AL.PHA A-LPHE

FIGURE A-12.1 NOSE EFFECTS FIGURE A

-- I F,. T 1'4, •I,

,--as~ - - -, L+'P'3sI - -. l-l-,l-,-.Fe,,-

S.. ......,:.. 0..45434L

-oI .. .. --. 0 6- 0-

-0. 4 , -0.5$OO

"",960 - -- - -0-9 3q.l-

FIOURE A-12.2 NOSE EFFECTS FIGURE A-12,5 NOSE EFFECTS

-- GUEIAt."BDY AIS FRCE&,.Ok -- IOlE E •.FFIT, MS.IL~RO..... X J 1YIN , BLUT/PONTEDNOSE

L . .F LI,. .

"6, To -- I

-10,1 14[134, OL" ~ ~ ~ ~ ~~~.0--,IOOOO•OOIO $00•,e SO03,0 • 5OOOOe',0 OO0I•O) 000•e03,O •

", RLPH •I.PL•,{ I~~~~-.00U9 -25 OEEFCS IUEAIO NS ET

-40..400

i.. ,, FIGURE A~~~~~~~~~~~--2N OY4ISFOC OI'T OEEFCS MSI- ['i' RLL 5, FN IFIN , BtINTPOITED OSE

:li 35 .101i

I.a. 00[ 0. goo•. .," " "10 ;. ; :, • .0. 00,,0.. ; - ; ;~ ; ; ,; : + ;• /; ; ;- ; - _: ; :• :• •• . . .

"1." 1' 2 00 2590 •-"00 M -560 ",0 5.0 1'00 11,0 2090 2 .0 I000 I.

. . .lit l II PL - - I ' 1O, 1F' L.. 110 F*.BL III,-pL

-- '0 F ,IL -- I--.- F3.0L-l- .-. O- - -l5OI+,0

0 Ils

•.ooo.• ' I ..'• .,.., lf

""-0-0 - -5..OO .

19e.seer- -

-5.0o Sooo 5.1. loo0 I. $¶I eo4o, 21.640 3oo0, 35. -I.ee sees5 5,ees 1 e as ses6 aMM e a15. ,es 3 3,FIGURE A-13-1 FIN EFFECTS FIGURE A-03.4 FIN EFFECTS

e..... Ilb......................

., es ..... ***O,'- -. - . -

-- I ,',I' L

$6.490 - - - -- es

"'"'"I"" -eIe0-------------------------45(..................,..............

- se esee s a e s s. - s e

"at$$$ 166 5 38,0100 MFIGURE A-03.2 FIN EFFECTS FIGURE A-13.3 FIN EFFECTS- 1 " - IllS IL!

-,O0 I, 3'L ll I

.................................- O5,O " ...

PIII

-I,0++ -l, t

ALPHA ,ILPHA-. FIGURE A-t3,3 FIN EFFECTS FIGURE A-13.6 FIN EFP•C';S

0.50.

FIGt.URE A-13. BODY~ AXLS FORCE & KO[1ENT PIN EFFECTS, NISSILE III, ..

ROLL 0, 3LUT y OSE.

36

- . , . . , - .. * ,

0. m

-- III,5'rI -- lll2J,.1hF *SI

,F. . . . .IG U R A -1 4 . F I N E F F C T F . . . .IG R A 1. 4, F I N E F F C T

.. . III fl .5,'F3S L -- - III.2,5*f3 IL

- " - -- . o ~ -

;B•• ,000~ - - . - .. - 10,00' - - -

/ -

0. /a D'." e•.,,e . .,,r ..,,.- - - - -"

-it 3-11L-

'•." ~ -5.6oe 5.ooe 1.65e 0o.506 l5.eeo 356o0e i25,6e0 :1o.S 3t0. -5.h 00 SONe 1,14 s~eeso iIoeH¶ o, eeo55 H1,e o~e

Fl POUR! A-14.1 FIN EFFICTS FIt•URE A=t4.4 TIN EFFECTS

- As * 14 O - ' HP

II ~~ ;~-- III'jIITTI1.11041 I L

4 . ., 2 S0 0 . - 0 . * SM - -- " •i M . . . . .

,",L .. 1 -4.400 0 . . ..

'IOURE A-14•2 FIN EFFECTS FIOURE A-14.b FIN EFFECTS

R O L 2 2. . B L U T N S E

.-- III, .'3.-,

"4'- I

-- **

• : •,0•... -- •-. . - ---- - -- 4,011 - .. -

• ,, ...... . . ...... "-- -... ... oeo - ' - "- -

-~ ** e e .6 " . 65 1, 50 0 50 , 30 50 ,, .•gI O * , _ _ _ .s , 25. 06 0-6

"*" FIGURE A-14,3 FITN E-FFrECTLS FI'G(URE A-t4.,b F'IN EFFEIC TS

S .,'./,.. •FIGUREI A-L4., DOD' AXKIS FORCE & MOMENTL T"IN EFFECTS., MISSILLE III,

+,•-, ",'.ROLL 22, B ULUNT NOSE.

.:. 37

- III 45IPli SI -- .1'45'IM-'11.'" ...... |l • S .L8 .... X I|, 4SI|IS----- 5, 3IL

1410o I M44l 8,011001,00-40

5.. -m cm -4-0- to0 e.is. -inm- --oo ,u.ow---'.il----- --

* *5 +-- -- •......

. -ussooo o.mo ewe ,. .~u.ewS,5l nomoo tosom, oos, -uoo oeom usoo eweoo l•1•ptosoo ne, owo ao ,'

F•OURE A-15.l FIN EFFECTS FIGRZu A-15.4 FlN IEFFECTS

14.d 01 .1 iol" -,,.I411 , - . ,,ii o., .I""~a o4,, II~ICU

+•. lOO , ,,,P~' , "'- Oplll-- ll l l '1434L I I II F0 4"

5-, , -- *, 4,200

44 - . -m C(- Ill -~~ -* ~~-5.04 6.0w Ism 184%ve IsA.Uus.6w nl rn-ow Iscow lr oom ijIee neW Iso s 16.9015

FIGURE A-15,2 FNEECSFIOIURE A-15.5 FIN EFFECTS

-"4'4 -."'I4IIII Il ,

4 o 'it - 4.. ,,,,. W

rIGURE A-15.3 FIN EFFECTS FIGURE A-13.6 rIN EFFECTS

FIGURE A-13. BODY AXIS FORCE & 40MENT FIN EFFECTS, HISSILE 111.

ROLL 45, BLUNT NOSE.

38

- HtII.'H'NFPT 7

* ........ !tL"OrFPT .....111.. t ,0, 2,,PT Pt'~ t ;

- I ItI0,FPT --- 111-•O 3,PT

0.ON -s- W

6.010 -1p~- I.NC~

.-- --- -- ----- -.-- we"/ ' -Ism 9s.e . -

, /e- - - -- - amK"

4.OO0 • -- ,.W 1164 3044 3.0 .-

Sq ..~~-omeo m.oN meom o*o mm lI ,o~m.ooo ,.om soam, s. -u nm.O . em i,.m mm •R is O~*.r*on o mum om as.

FIGU' , A-16.I FIN EFFECTS FOIGURE A-15.4 ?I• EFPFICTS- I 1 'N .!- lil't U f t"*II I" " ' ' " 1'"-" ."

AM .. I a. 4'1

-8 .0641 ,.4 3.40 loe,1M W 2100 W N3 .-. 40 $ W ol o m 1 s .u t I14

.. off

$lost

-5.oo, mowoo u. iom, IMAgING0m a1.606 WIm a. -m.oNo 0.m M .o soee a1mo.3 o 2 ,Of n. , 0 0n.

PIOURE A-16.2 FIN EFFECTS riOURZ A-166, PTN EFFlCTS

-" i o his

"l • I " O -~i II I"-i

-I .Oi-O.

"-mir - " - - - ~ -I, -

FIGURE A-16. BODY AXIS FORCE & MOMENT FIN EFFECTS, MISSILE tI,.

ROLL 0, POINTRO NOSE.

39

I a. a600 to M

-0OW -- - ~1-

.1 014*Uil~~t 0,

4. Me Calf **~

1460 .4e~---------------

Aj w"Ns 6663. 40 .4 . as 3

FIGURE A..17.1 FIN EFFECTS rIGURE A-17.4 FIN EFFECTS

- ' , 14P0

-eer -- j:444jjj-0.4 .4.100 F~...

Bisec -J - F- -

-6.401 -

FIGURE A-07.2 rim EFFECTS FIOURE A-17-3 FIN EFFECTS

OF I UR 0-? 0OYAl OC OWTFI FET, MSIEIIROLL1 22 OITRfOE

40O

tern- ---- ii.6e -

1 6. W -a- ---.... 9- e~e. A#

FIGUR - -1. FI -rIT FIUR A.8- FI EFFECTS-

- - - * -see

Ism___ - - -s$as

6.4K - -- 6-408

-Isew ewe" Som e9m 1UPWe~ -low Sim l u ow urns e "m S¶wa.eol m 49 orn1 410.06 1fIGURE A-16.2 FIN EFFECTS FIGURE A-18-3 FIN EFFECTS

II I1i~H II~t Ji4

C t.66 to- .

FIGURE A-18.3 FIN EFFECTS FIOURI A-16.6 FIN EFFECTS

FIGVUZ A-18. BODYi AXIS FORCE Is MOMENT FIN EFFECTS, MISSILE III.

ROLL 45, POINTED NOSE.

LI 41

- . '...,.,L - h.h.'N74LS ..... I II.'N41 Ol -- .... "| • ,,"1

-... utI B-PI. I'X.L ----- I lal-t 'a-NP,

- -- I U'.5' NP I L• i/ IUll Si• /ILj l .

-k

5, N --- - - - -a --

- S . O ~ s , •o m o H ,• I S ~ a m O .• n .- s me w e se a se a swO ~ams n w.~m i s w 1 5. ,

FGRE.Vt A- tg.I BODY CO RNE, I R AD IBUS EFICrrl{TS FIUE'11r~ A-19,. BoDY CORNER R•AD IUSt IEFFEC"TS

I U-01. ii W IL

4. -

I .559 - - - 2, SV ' -"•

1, ,.,9, . , ...7 - C a.

36/ 4.w

So l I I..

e e e --M o o ,- o o , , o IB, i L -,e O B ,Oei e O e B --e . os~ , ,- -~ o - o oe • . e .oo . oo - * O - S

FIGURE A-1 0.2 BODY CORNER RADIU S EFFECTS FIGURE A-19, . BODY CORNER RADIUS EFFECTS

*°° al"i' nu. ii' aa| d.,.

-L

-I.V. , % '..C

V..

"-4a e eO - - - -O

V..*U5UR- - &- 9, W: A , -OR e'- I.S5A -OD -|••C E -. - -OL -,-.-., -

4.2,

low

sc s-.. ~ a

* -4ess--.-.-...........................................I0

*FIGURE A-19.2 BODY CORNER RADIUS IFFECTS FIGURE A-19.3 BODY CORNER RADIUS EFFECTS

Y,42

k* y 4 a a..~. a b 4.. --- ~ -. ,-* -V ..- . .. w . . . -. . . . . . . . .

4.60 Ism W -~- -

*.* 0

SW - v -4

-5.40 4.11 sSN 19.0 It-60 im lt ls"14% [email protected] 1

FIGURE A-20o, BODY CORNER RADIUS EFFECTS FIGURE A-20.4 BODY CORNER RADIUS EFFECTS

- lIoITwh.............. I jraL a-. III3,001f

WIo

- - ~ ~ ~ ~ s of, ~I i - v # m

I.*~ ~ ~ ~ ~ ~~~~~o 01~e 310-------

41600-

-, aesi Cj ~ .:.One

is 4 06 ow S"$ oom Is .-5.000- 6.0 149 loo -1 "40 0400 ".0 -5 -k~ "6 o

-100

-1.400~ ~ ~ ~ ~ Is.sm1.00srft9 1."3.6 5 -8.0164 5.41 - S-11 -1 1,0 1.6 1.0

FIGURE A-20.3 BODY CORNER RADIUS EFFECTS FIGURE A-20.6 BODY CORNER RADIUS EFFECTS

43

- ~ ~ ~ 1 ,sIaI1SI -'P0

I'M op UZI.. va

'-'fot

..*... ...... 1, 51 NOIVM l

4.6ft. .10c lo

0m e.sI*.fN, aIms 36.M *$Is lmow $@41e604w oLaetMI sm i

FIUEA-11.2 BODY COOPMR RADIUS EFFECTS FIG~URE A-21.3 BODY CORNER RADIUS PIT

If~ IL- I'll $I, 1

ft * v - .W - -4.040

4.441 - - - . ~ Ca

- - ~ .-. 00 -

FIGURE A-21.3 BODY CORMER RADIUS EFFECTS FIGURE1 A-21.6 BODY CORNER. RADIUS EFFECTS

FIUR A-21 WIN AXISI4 FOC iOETBD -FET, 11 ROLL ANLEWINI 1, BUNT OSE

2d'I dI444

-. 1I ILI

to,

-- l" "3|,P$'P.IL -- I.33:•P..FI.I3L '

'Se" SI"o I- ". I - 0- 1- I4. no 1 I..I l n.

.".l C01 A-2 - -RNI, -A U E - -B -R -

:~el 14, e4 /""le lk

4.1 C

1.001 - .- ,C C ieee -- - - - -°-

-,11.10 1116 110 Ill o Isom 3610 1 1180 480 11,"I-M IU % I." 1.s 00

4,0 ..........

-1,ooo 1.88, o .001.08 6, i 1•0.o, o 1.,00 31,o0 35. -1.see of .o s eeo M i•i•j is.oiiso .,0s o 36, "1 3.,FIGURE A-22,1 BODY CORNER RADIUS EFFECTS FIGURE A-22.6 BODY CORNER kADIUS EFFECTS

I A'-l22' ,'L A, IFC'MY F33 ROL ANGLOiii 4,1414 1 Iqlp

* .'_ - - - - - 0. 4 W - -. ,'+- -

FIN . ...... ., .... aOS

:: liii - h45

F.•IGIUR! A-l2,2 BODY CORNER RADIUS EFFECTS FIGURE A-22.3 BOD'Y CORNER RADIUS EFVECTS .- , I l +'31$ S - | i43PI 'IL

C l. l -- It- U3PI,'~I/S

*4,101 -- ...........,. .......... ....,...**,.. .,

- -

SI--

- - --- --l00.C -++o l ._"

• 1,00 0,00 li 0 0. 000f~l IU.¶l llO.lO 35,000 i5,00O 25, "5l05 O ,N Iiisl lii,n II, ¶ISM*J500 *0.00n 30.040 30,

,.' FIGURE A-22,3 BODY CORNER RADIUSq EFFECTS FIGURE A-12,6 SODY CCK(NER HADIUS EfFFCTS

;L' " '" FIGURE A-2L, WIND1 AXIS FORCE. & MOMENT BODY EFFECTS, 33 ROLL iNGLE.,

' "', ~FIN 1, BLUtNT .NOSE,

• .i 45 "

-**I~ .~**'*-P,*~* .. . . . .

9L,Ij II

Is M I I13,061'P

6.00 M.--- - Moe

-

....... ..- 0

4. M - L 0-

riouRE A-23.1 NOSE EFFECTS FIGURE A-.23.4 NOSE EFFEC(TS

Ismi- - - - 4. M -


14 :..t..

L-,0 -C t.6 - - -

-le 600 - s - s Itel -5i%1 0 15013.- -see -$, -. 1.00 -08 - -0 46fl"3.0 5

FIGURE A-23.3 NOSE EFFECTS FIGURE A-2.).6 NOSE IIrFECTS .

46

II~I.,,,I

--. tI t,2 /FIh'P? - | 1IIJ$/Ft,pX

c 55f -4 c550-

5", /

-01 7.,. L --- -*.v

-5.00 low 5 0.55 Is-of 14%9I nowe HM 1 8."1$W om14 ow8." 60 5FIGURE A-2.1d NOSE EFFECTS FIGURE A-24.4 NOSS EFFECTS

"... S eA ....-

W-- ~ -4.W-

-Ie'M sew I'u1.ewse Warml~a.W5lss M W 36.4 -se sees0I. sew esse IMP~e~s M sse M eWs 31.16

FIGURE A-24-2 NOSE EFFECTS FIGURE A-24..5 NOSE Bpe l. CS

K . -X- -

iiel i

4.5ff - -

-Re.r -~ m _,,,_•m " .- o, - -, -,.e e mi,. ,, *m* -- , - ,,- -

-aw - -"- - -• -a.sa -~-- -

-I'Ms sew s.ees f Isewj~a se oe n -4.ew 9.6w sew aslew I5~~ses nwes

FIGURE A-24.3 NOSE EFFECTS FICOURE A-24.6 NOSE EFEiCTS

-FIGURE A-24. WING Axi1s FORCE &MOMENT NOSE EFFECTS, MISSILE 111.ROLL 33, NO FIN/FIN 2, BLUNT/POtNTED NOSE.

47

I Ol

4.0 1.00$,~I'L~jI~l-II

5.0 0.144 5.8." iL~s %m cl 5 owl 5 .4 4.609l 5.046 06 1% oW1.083L4 5

FGR A-I'25P.1 OS EFET F IGUEA2.4 NOSEEFFECT

Is..,---------------------------------Ii*OC

1.014- 6.4- .N

FIGURE o,.25.2 NOSE EFFECTS FIGURE A-25.3 NOSE EFFECTS

4.866- 4.4

IT.

P, ~ a e -49 -.6 -.109815T14.6 Rom wea 35 -5 on I eW1 sb$W assim 11


FIGUR --5 WIND AXI FORC & OETNSEEFCS MSIE11

ROLL11, IN 1FIN3, LUNTPOITED OSE

seer- - - cec - -48

- II ~ I LIIII ý37,F 'PLI I. 33,.1. P1 pT ........ 111 .,; "FI1 1 3 .... U . • [L ----- I11'"13 F.1 &L

I- JI F3 tr? III.334F3' T

. .. -I_*Q., - -

. ,,. -,L+ .... ..... ... / . .I"7"• -• '•-•- - I, hl.OC....... ..It- -tk 11.1.000

- .--

0.000 5.000 10,000 1,20 .99 35.000 3, 0

FIGURE A-26.1 NOSE tFFECTS FIGURE1 A-26.4 NOSE EPFFETS

,,~ ~ ~ ~ ~ 1 F+ , P++' ..........-+.-•4S 0

0.~~ 4k0- -

Ice":

0..... .. .000----- -

.0,04

-.5,+00 , 0.0 0 o .000 0060 t5.$j~1.000, 16...,, ., .00, 35. -5.6 .0 0.0 is,o I.,oo I. . ; a. ," 4.10. 300.00 35.

FIGURE A-26,.2 NOO EFFECTS FU A-26.$ NOSE EFFECTS

"•~4 ...... •|I ll3,e3l,"

J-- - l -• - - l r.000- -

ms.0 o0 5. 1. 0 0 3o.000 33. -5.000 5.00 $A 10.06 1ow . 29.too - 5.0o0 30.000 35.


*FIGURE A-26- WIND AXIS FORCE & MOMENT NOSE EFFECTS, MISSILE 1I1,

ROLL 33, FIN I/FIN 3. BLUNT/POINTED NOSE.

49

- .. . . . . ...- ....... j '*,***,,... . . . .

111"11.28I ,l t'143/ I'l : I I LII IIF /Ii sI. I f f 1 5N. l'6 8U U

..................... MII ..[[email protected] - - I-om t • - , -

C j .e se o, NC t ,.es+

L

C . C Ut -I SSC el - - - - -•

FIGURE A-27.1 FIN EFFECTS FIGURE A-27.4 FIN EFFECTS

, - ... ....

S.W - - -- "

.660-1.6

C.., 1 -- - - -. -4-4a

S1,6a014 i .l'. -a a

-4.1"T;

-8.4en M5.1 MMe sm iL all$" 111~.001 30.406 3e. 9.sM -se em 6 10en 11een 16$ee. Mt.e mee new.

F.OURK A-27.3 FIN EFFECTS FIGURE A-27.5 FIN EFFECTS

FI•GURE A-27. WZIND AXI;S FORCE & MOKENT FIN EFFECTS, MISSILE 111,.

R O L Lt 1 1 , B L U N Tc NO S E ,,. i - •

50

-' ,' , ',", . '- -. , ,, - ..m• . . . .i . . , . ,. ,:.;:.,", - -".I .",.t,• ....i:.., ,- + ., ., • .

" 111,4 3 ", 111 , HF '9L-*-".". ...... 111,/33.;'5 F1-'IL ........ I Ib,13.?t, F .Ill1-- 111-,------,-3--'-F,,-oL

L/

, .., ...

.. ,.,c-. ,.O

k4

45.94e 6.606 5,000 16100$$$ 1 446Hil 30.0 6.108... 35. .-5.08 1-6.0 8-04 1ON .066,00 6060 1.002.60 5

!,1 .00'"t '2 .6 25... . 36.0 0 3-5.•" -

FIGURE A-28.1 FIN EFFEICTS FIGURE A-28.4 FIN IIFECTS

,,"" I • "3••H :.

-.0 - -- -1O.000

-66.0- -- -400

-5.666 6.60, 5,66O 10.0H0 11 620,,0O0 1ISSH 360 35, -toOO I.066 M .000 16.00 "A¶I, t&' 0,1 5,000 3Oo. 35.

mAMA

FIGURE A-28.2 FIN EPFFICTS FIGURE A-28,s FIN EFFECTS

1a111! 11,11L o1VML • L

,,I' I-3.'P3' , , --0 .. . ,

C.0 6.009-----------------

- - - - - -O- 4,ar - - -....-.. . . ..

i• o , ' --' -I-"---

FIOURE A-2a.3 F'IN EFFErCTS rIGURK. A-2•,6 FIN r-FFlCT3

ROLL 33, IILUN! NO1E1

4.0 4.0oo1

"0.000 else$I0

-- '-2.009 -a see • .• mm~

:l FIG;URE A-28.3 FIN KFFECT$ FIGURE A-28.6 FIN K'FFECTS',

'' ... 'FIGURE A-28. W IND ,AXIS FORCE & MO KENT F IN EFFECTS, MISSILE [II.

-. • ROLL 33, BLUNT NOSE.

- IIII.' IF 'PT .....

.--- Ill IIIF'•,sou --- tilr•P:'i.": 112/II'1Pi'P?

0..f- -

_.•~~ ~l t6i lll"

-8.666 4.ees 5,ew 14.4e ilL141.4 25.ses 3ss .s:s 31,-10. 0.mW30 00001 W$$ $ 9~~0 m1s30 35.

FIGURE A-29,1 ?IN EFFECTS FIGURE A-29.4 FIN EFFECTS

'. - , .-- ,e er -

6,001 -i~ -ll -l . ..

C.~4 444'5,

S-,,, ,. ,, •,. •.•.,,,, -. -,,. s.ee o, - ,. ,, i~- ,- -, -,*.

1.0000 ,, .091,0. AV4

FIGURE A-29.2 FIN EFFECTS FIGURE A-29.3 FIN EFFECTS

6.4.06-

alo 'S0.

-2 00 -1.'

.6,

C -

S,,eoer - - -- - - - seee - ---

"- - - -... ..- -1. - - - - --TED-- -

S- 1 - - - - 5 -4,2 --

-1.6.0o ,,.00 ~,,,o 1,30,oo.0 ,38•.oo.,3o0 3o3~.,3 -3,.o0 3,.30 3,.50 6,o,. AlIA .,0o 3.,., 2.,6o.3,

FIGURE A,,29,3 FIN EFFECTS FItGUREC A-29,8 FINI •F'FECTS

FIGUM.-29--IIllXSFO"E 6MO"ET F -EFETSt MISSLE II

,~~. . . . .. . .. .. .. . ,.o

SWI4 W*. ,Iii '.2-.''.~.* ' - ,, ~ .,. . .. . . . . . .

-•- ! 1t133,FV•,'PT .. .. 1 !,'334 30 TPy'o."".' _ I !/3f3p •--|!t3l rP

S1p

L c

_.,oo Z.

w%&M IN 20011006 3. 31 M 4.000 sow0 *11.11,bo .01136.1100 3',FIGURE A-30.1 FIN EFFECTS FIGURE A-30,4 FIN EFFECTSI....I'ifLI!1i'"P III ;M"/!-P.... .. ,, + .. ...f. +

O Cci - 4,1)1ff

4,Se -4, - - ---- .

ym --.. --

.• i,,.,0 - -,- -

- 4. M

Oli

-11'" 1 sow w0.0MSS 30. -sow cow4 Is' oo is.$$I"o ,1 1n.e 36.ow x,

"FIGURE A-30.2 FIN EFFECTS FIGURE A-30.3 FIN EFFECTS

4 4.060 - - -

- *........ Mp.I ta.0 I.

-. 6800

RL 33, PONTE N

0.,01 - - - - - -0, l -- - ,.5

• -4,1111-4.0,.0.-s,.o0.s sa., messea is,.~o11s no,**c asses soo 38. -o,*e* o,0. sew* toso. -~oa,ooe•,-,* aeo 2,,o.,S ,..FIGP•URE A-30.3 FIN rFFECTSq FIUE'+. LI FET

FIUEA3.WN XI OC ONIFINUREFFECTS, MISSILE I TI.

ROLL 33, POINTED NOSE,./

53

................. *.. ~. *,. *~~*.W7

\ .~ ,-.<-.

APPENDIX B

TABULAR LISTING OF FORCE & MOMENT COEFFICIENTS

The force and moment teats conducted on the missiles of

- .inane*& ratio 8 are briefly described at the beginning of

Appendix A. A total of 66 tests were conducted. Printouts

of the coefficient data are illustrated in Figures B.l through

.B66. Figures B.1 through 3.40 illustrate body axis data while

figures B.41 through B.66 illustrate wind axis data. Table B-1

defines the nomenclature used in Figures B.1 - B.66. Tables

3-2 and 1-3 describe the missile configurations tested in each

of the 66 tests.

54

'.'4.

'.

* a

'4j"

4,j

ALa *9 , . 9 . .9 9 . . . o"*. . 9~

4 9 . * * 9 4 9 * , . . . . . .9 . . a * *. . . 4 , * . .. ,

TABLE B-i

CA -odyAPPEDI B NOMENCLATURE

CA -BodyAxisAxial Force Coefficient

cc - Wind Axis Cross-Force Coefficient

CD - Wind Axis Drag Coefficient

CL - Wind Axis Lift Coefficient

CLW - Wind Axis Rolling Moment Coefficient

C14 - Body Axis Pitching Moment Coefficient

MW - Wind Axis Pitching Moment Coefficient

CN - Body Axis Normal Force Coefficient

CNV - Wind Axis Yawing Moment Coefficient

CY - Body Axis Side Forces Coefficient1

ROLCO - Body Axis Rolling Moment Coefficient

YMTCO - Body Axis Yawing Moment Coefficient

a,~

*1.A

!'.1

,Ii

,o,

- '". ."

TABLE B-2

FORCE - MOMENT TESTS

(DATA PRESENTED IN BODY AXIS SYSTEM FORMAT)

Id* Roll Fin** No***** Appendix Figure

1 0 N7 BL B-1

1 220 NP BL B-2S450 N7 BL -3

II 00 N7 5L B-4

11 22° NY BL B-5

II 450 Np BL B-60I OS NP BL B-7

11 220 N7 BL 14

111 450 NF BL B-9

IV O N7 SL 1-10III s 0N ? PT B-11

111 220 Np PT 1-12

U4 45' NF PT B-13 --I O11 BL 1-14

I 22' FL BL B-15

4 450 Fl BL 1-16II 01 71 BL B-17

II 220 Fl BL B-18

It 45° P1 BL B-19III 1 Fl BL B-20

UT 22' Fl BL B-21

IT 450 F1 BL B-22

IV 0 F1 BL B-23

IV 22' Fl BL B-24

IV 450 Fl BL B-25Ut 0° P1 PT B-26

III 220 Pi PT B-27

II43 5e Fl PT B-28

"56

TABLE B-2

FORCE - MOMENT TESTS

(DATA PRESENTED IN BODY AXIS SYSTEM FORMAT)

Lody* Roll Fin** None*** Appendix Figure111 0 F2 BL B-2911! 22* F2 BL B-30

,,ll450 F2 BL B-31

0II 0 72 PT B-32"II 22* F2 PT B-33

, III 450 F2 PT B-34.'I 00 F3 BL B-35III 22* F3 BL B-36III 45' F3 BL B-37

0IO F3 PT B-38""II 220 P3 PT B-39 "4P i l450 P3 PT B-40

*Body Configurations

I - Square11 - 102 Corner Radius

III - 202 Corner Radius"IV - Round

**Fin Configurations

NF - No Fins AttachedP1 - Fin #1P2 - Fin #2F,3 - Fin #3

"***Nome Configurations

BL - Blunt NosePT - Pointed Nose

4 5

TABLE B-3

"FORCE - MOMENT TEST

(DATA PRESENTED IN WIND AXIS SYSTEM FORMAT)

Body* Roll Fin** Nose*** Appendix Figure

I 11e NF BL B-41

1 330 NY BL B-42

II 110 NF BL B-43

It 330 NF BL B-44

III lie NP BL B-45

I1 330 NF BL B-46

* III lie NF PT B-47S1 II 330 NF PT B-48

. 110 71 EL B-49

I 330 71 BL 1-50

110 p1 BL B-51

-. 330 pi BL B-52

111 110 F1 BL B-53

0 I 330 71 BL B-54

IVe110 71 BL B-55

IV 33* 71 BL B-56

11I 11i F1 PT B-57

I1I 330 71 PT B-58

Il 110 F2 BL B-59

III 330 F2 BL B-60

111 ii0 F2 PT B-61

III 330 F2 PT B-62

"III 11 F3 BL B-63

III 330 F3 BL B-64

III 11 F3 PT B-65

III 330 F3 PT B-66

*Body Configurations **Fin Configurations ***Nose Configurations

I - Square NF - No Fins Attached BL - Blunt NoseII - 10% Corner Radius F1 - Fin #1 PT - Pointed Noae

III - 20% Corner Radius F2 - Fin #2IV - Round F3 - Fin #3

58

'-IM I-.S 1. F I ROLI 0 Nn rINSY TI, pT NO pF - IOINFI L,

RUN NIUM•R X 7DATA TAKFN 17:035" 06. HAR-RO

COEFFMICEENTS AIOJT TIHE DMDY AXIS

ALPHA CN CA CY CM YMNCO ROI. CO(D£O)

0.1R 0.000 0.144 -01006 -.0640 0,0.0 -.04011

&2025 06136 0.147 -04017 011911 0*02A --0#014I,.

4.1 4.25 0,296 0147 .-04023 0 ,)10 0019 -0,019

0.7 O429 0,142 -.01029 0ý7o.723 0.01? -0.019

a 1.20 0,4690 0#149 .-0,074 14120 0022 -"0.026

104,23 t'2~30 01143 --0,044 1.194 001.7 "-0.029

012,27 0.023 0,142 -0.047 14130 0.014 -00033

14. 7 2.7 1,181 0111210 -.0,091 1,428 0,040 -0.037

15.73 2,A2 . , 0.08 "0,097 1*64"w 04047 -0.03?

17 3.004 0.070 0)"47 2.061 0.044 -0.038

.. •0. 6 1.43 C 0.000 "-0, 17 2 ,4 0,074 -0.038

222•,27 3,641 -0,024 -0,206 2,944 0.1.13 -0.039

24.28 3.920 -0.034 .-0.270 3.444 0.j77 -0.0073

26,26 4.277 '-0k093 -'0.74 3,944 012 -0.033

2.1J7 4#5"1 "0. 51 "0,37n 43 57 0,P 7 -0.030

30.00 4,696 .0.164 --0.#413 4.70n 0.*30 -0.031

Figure B.1. Computer Tabulated Force and Moment Data for Missile I

Zero Degrees Roll, No Fins, Blunt Nose

594..

HMI SILE I' RnIlI.. 2 .,! N140 F.IN 1I. UNT NOS 1/2, 1/ !/NF/-I

RUN NUHMIUR I'S 8DATA TAKEN 13t'1, 04M,-MAR.Fl8O

CO0FFCXNTI ADMOIT THF 1RODY eX1S

ALPHA CN CA CY CM YMCO ROICO

(DEG)

-0,04 00:14 0,33) -,.04018 -.0*055 0Q053 -0.,010

2.11 0, IVI 0,142 --0.4016 02. 2 1 -'.0 0"3 -0,016

4 245 0°430,1 00•.'.43 "-0 0 1 F 1. 0 4 Mt -.04 10.6, -.-0# 0 7

6.12 0,404 0.1411 -'0 '.2"R 007,'$0 .0.'60 -0#020

8.22 00692 0 o 143 -Os 42 A . 05.9 -.0.314 -.0,016

10:2M 0196"1 0 1,29 -.0,61.l 1 s367 -0.47,1 -. 0011

12 2 7 i .-o, nn ,1 ,704 -.0o 1.)1 ,.O#OOJ1• ii

14 27 1,1.71. 0,1,07 1"'210(t 2 0 1, 6 --0 ,497 04 Ot I

16oJ7 ,1,860 O.O.7 7-1. 33 2.317 -'04430 0.001.0

S11 2,140 0,064 -1. 93n 2 v666 e -0.07 0.020

19,77 24.1S 0,040 .. ? - 34 IP941 '-0 170 0401B

21124 2.' ,71 0.01, -"3 046 1 3 91 0,117 0.009

24.22 t. 01 0 3 r -3, 7756 3.807 0 412. --0.013

26*24 3 .662 "0",j4 -4 414(1 4.2'3 0 671 -0,044

28 29 4102 -0. 1 ,116 -5, 167 4,631 070 -04074

30.00 4I50,1. ,.1e0, 8 -,7),86 4,974 0 ',SI 0,,O8OFJ4

Figure B.2. Computer Tabulated Force and Moment Data for Mismile I

22" Roll, No Fius, Blunt None

60

,•,", ,, .• .. , ,• .•\ ,,,.,.• . .4,•, ,,.., , ,,.,,i., .:,,,.. ,i .i .. . . . . ,. . .. ., . . . . , . .. ' - . . - .

MISS ,IE Ip ROLl. 45r 1N4 FTNfr .IINT NOS - t/4 1/NF/RT

RUN NIMPER IS 9DATA TAKEN 1.31.741 06,MAR,,RO

COEFFZCtrwnT ABOUT THIE 10nY A:XIS

ALPHA CN r'A r.Y CM YMHO ROI, CO(DRO)

-0$19 0,032 0133 ."..0403 -0,036 0.071 -0.009

2 ,33 0 t1 11 0 1143 -'0 160 0 13 '0 , 161 ".0,01A

4,33 0,256 0148 "-0,2)9 0.30" -.0348 -0.018

6128 0.4051 0k.140 "-0 144 0 f49W "0o,•71 "0.022

8, *23 0.619 04j 2 *04641 09792 -0,#77 -0.027

104 1 2A 9iS7 0 0 L -.019980 1.4581 1" -1.0099 "'0 603t.12.3 p r, 0.097 -. 1,241 1.014 "A -.1 91 --0#040

14 15 11I, l 0 019:1. -1,,94 1.32 "',3• -0.046

M7,71 2,#75 0,2 6 "2 7.6 7 , 149 1? 0,f94 -0,-055

20J 8 2,p14 -0.014 --2.808 1.739 -. ,187 "-0o059 '

2,1 2.2 3 31,0 "0 0"6 -.3,340 1.1710 7"3079 -0,064

24.19 7.9 14 "0 ORR ".3,6 0 8 'P, 5 5 " ,91p A '-.06066

26623 4., 4 3 "o'132 -"4 ,4 73 •1. 1"' .R602 -"0,069

28071 5109? -0.190 "M10t1 2.69R -2 937 -0#070

30.00 '.674 "4 14 11"') 3 A00 "3.2S6 -0.066

Figure B.3. Computer Tabulated Force and Moment Data for Missile I450 Roll, No Fins, Blunt None

61

MI99Y1.E TIP RnL. 0r NOl FINSP KI.NT NOSF -. 0NFB

RIJN NIINDER 13 1.DATA TAKEN 09MM47 06--MAR-9O

coPRmC!VNTS ABOUJT THEC MYV AXIS

ALPHA CN r.A CYCM YmcO RM.ICO(DEG)

-0.01 -0,044 00148 0.016 -0412.5 0.007 --0*011

2,34 01109 0 1 ,9 01010 00084 0.003 -"0#015

4.40 0.247 0.152 0.009 0,477 01002 -0.04060

6,2.27 0 036?2 06156 0,006 0 *762. -04006 -0#021

9.20 001530 0.146 -0601r) 11029 0.001 "'0,023

10.12 3 0#844 0o 145 00046 ItM3 .000O1 -0.029 _

1*9 1.219 0. 143 0#112 14439 '-04116 -.04026

15.71 1*723 0.089 0,117 1.897 -0#153 -0.023

17 s 82 1 199-i 0.071 0.111 2,207 --0, 1 7 --0,024

19.72 "1.133j 0.021 0.134 24420 '-0.381 -0.0623

22,# 13) 02,771 -.01023 00100 12o70F0 -.0,1110 --0*027

24.23 3 4 j V -04081 0.08 2, 5'26 '-0.1116 -06026

26,28 1 7,512 --0010'. 0#061 3 42 "1 -'0.1~7 *-040%9

29,.20 3, 89.1. -0.146 04049 3. 457 --0.144 -'04015

30000 4,271 -'0,104 0,007 3,734 -0 #12S "-00006

Figure B.4. Compute,' Tabulated Force and Moment Data for Missile It

0* Roll, No Fine, Blunt Nose

62

MISSILE TIP ROLL ., HO FN N, •s PILINT Nn- . 5iN/1L

DATA TAKFN 101N33:317 06-4IAR-80

COEFFICXIENTS AW)IJT TI1F DODY AXISALPHA CN CA CY (11M YMCE) RntLCO(DEG)

0.03 -00023 0 01.5 0 0.021 -0,092 0.0 " F .000. 00

2o39 1tI3 0.61,"; -.0s013 0.191 -0.0 00 -.0.015

4.27 0 020*%i 0#.144 -0.077 0.424 --0614T' -*.0 60:0

6.20 0,327 0.145 -*.10 b0.62 --Oi24A --0#0248.21 0.s4 T1 00150 *"0.61. 0.9D#67 .-0.341 --0#02S

10+21 0#701, 0.143 -'0 o4PR 1 2.56 -. 0 t421 -0#028

12.30 0#941. 13# ".0 52 1* 5 45 *i-0 o442 --0,023

16.29 1*426 0+104 '21.3 0 2.142 -06306 -0.028

41

17#71 10593 060n2 --1.472 1 2 .36 4 -.0"19s -0.029

19476 1.0 0. 04"? .-1 #R90n, 2.721 0.041 -0#04022A27 1,E241 0,041 . 9 5-A 0,430 -0

24,24 2 6 !30 00014 --3.#262 3#474 0.79rs -0#084

26,0 -0.021s7 R .,01 -4,011 3.843 1 1.10 -0"t12

27.76 30. .47 -0.047 "53P 7 4.607 ".297 "-0,129

30.00 3 S610 -0.0 A It -1,.#299 4,377 1.363 "00150

Figure B.5. Computer Tabulated Force and Moment Data for Missile II1,22* Roll, No Fin., Blunt Nose

63

MISSILE IIP ROI... 1.- 3 NO FT.NS WH.tUNT NOCF -.. 1I4SINF/PL

RUN NUMIIDR I, 3DATA TAKEN iOt4m'ti2, O.-MAR'-SO

C'FFI"CI.iNTS ATW0UT TH' nDnflY AXIS"ALPHA CN r, A r, CM YMCO ROICO

06 (DE 0.2•F)4 Od.4A 04169 "0.320 "0, Oftl --0.008

2°3." 0, 360 S ( 4;N 0 094 -'0.09,0 -0.340 -0.010

I 4,37 0.432 0,150 -0,27 0.109 -0 .4'.0fl -0°015

S5,94 0 , N44 06 't,11S -'0 , .10 0, P105 -'0. ,63,5 "0,017

8,28 0,707 0.132 '-0' 7,10, 0,493 -0,0 t -`1. "020!

10424 01920 0 .1.2 '0•.0 1 ,'00 0,671,' -- .-031 ""0. 030

12.29 1,147 0o124 -0 1794 0.R96 "1. 12 .0.076

.' 1411ZI 1. ,4 2 0.:1,17, -. `1, ý13.: 1. b0• 201 `1. •1. 0 '-0*044

. 1.5,74 1. 6r14 06J00 .-.1.140! ,1 #170 --A 31 25 -04,0494 ,I

17,7n 2.000 007? -1. 717 1,2 -I .'1, 44A -"0°06

19,"K 27394 0.0271.!") -2.43 1,2 1 .332 "1,072 -"0,055.22,8 2 9 960. '.0, ,0.5 --. 78l2 1. 472 1. 610 -0,054

4.'424.*22 77 4 41 -04061. '-3.3401' i6 9 7 -'17ri -,060"55

.4 28OP9 4. 80 -0,1,04 -"4 4 462 :4297 -24 .140 '0.060

30,00 A 075 '0 0.01 -4 .?2 7,04 8 -. 2. 40,1, -0059

FIGURE B.6. Computer Tabulated Force and Moment Data for Missile II"450 Roll, No Fins, Blunt Nose

64

MIS .SI..F T TI , RnLL O NO F.N1 T.41 IUNT N4OS3F .T. 7 /OiNF/F.:I.

DATA ToKFN 11:•.2147 06-MAR.RO

CORFFICIITT i).DOIJT THE qOP'Y AXIS

V, ALPHA C N 0A .Y r'( YMrn RO. Con(DEO)

-0,10 09003 O,14, 0.004 "0.107 0.013 -0.007•4 I'l 0 4. 0.* 1.4 4 -.0.#002 0 4 M!9 0,017 "-06011 •

4il .1, 0 Pel 0,.147 "0,0 ,17 0t .4 0,024 -"0.014

S'1 0.377 00,4 O1 ," 02 " 10, 3 . 77, 0.430 "0,01a

0 17 0 r,2~ 0,140 .-0 0'33 1 0 31'l 04,031 -0#02'0

10 , 27 3 0 * O14It -'0 010 11 1306 Q0.01 -0*025

121.41 0.4 9 0 1 ; r -00033 1 "a7 7 0.047 -0,029

13,94 . OZ•7 0. 1 3 "'0,041. Is 0.0 0 "0.032

16,05 jI2.09 0,104 0o04r) P .A02 0,062 "0#074

17.1*17 3'1. 7 O00 4 --0,044 Ill "1 0,0651 -'0.037

19,7, 1 36 "A 000 ".-0#0, 03090 -0,041.

21o 20, 1,779 0,3 0 1 .0 0,011. 31050 0,077 -0,047

24.P4 n'.008 0,004 ','0,06(,;I 3.300 0,105 -0.049

26o27 ,2. , 2. 14 "'0,0 e '00 31696 0,071. -0,0.95 0

28, J19 2#431 .-0,0,9 W ..0,032 ,,T7D 0,074 -0.007

30.00 .2 640 . 091, .0 0 !')- ,114N9 0,122 -.00718

Figure B.7. Computer Tabulated Force and Moment Data for Missile Ill0* Roll, No Fins, Blunt Nome

65

•'•• '-'.. ... ",-• •- -:-_:-, 4 ' • ".* . ._' .' " .; Q .'9, ,, ... , *.', '* , "A •"',, "'2 " " , ' . ,.oJ

* ~~~MISB!IFE 71!P ROLL, 22*.5, Nn FINS) DI lINT N- 7/2/H/n

RUNM NUMBER IS 5DATA TAKEN 11U41116 06- MAR'--8

CdEtVICICENTO ADOUT THE VODY AXIS

ALPHA ON CA cyCM YNCO ROLCO(DEG)

-0.01 04130 0.123 '-04062 '-04019 0*031 *0 #0 0 1

2s43 012119 01140 -.04126 0,270 -0.060n9 -0.007

*#4448 0$360 0.139 -0.1487 04,122 -00179 -0,0I01

6032 0.447 0,13.1 --0#229 0.o752 --0,263 -.00015

8.26 0.5458 0.139 -0 t270 1.006 -003152 -.04020

9090 0460 641 1o34 --0#.17 1.0211 -'0. 41A -0.027

12430 O.8789 0.131 --0*474 l1499 -0o4flO -0.632f,7ýv

13.71 0199,4 0 tI10-0"'0,172 1,471 -0.o489 .-06036

4;16.30 1.2J1 00091 --0#793 1,956 --Os443 --04043

17*74 1,o32.4 0 P07", -.00933 2.0112.6 .-0.6303 -0.046

19$90 J1.500 0.060 --1,10I6 2,424 --0#24T --0 .05~4

22*23 1,717 0.037 -'-I 1,2 7 2.*004 --0.021 --0,064

24.s23 j 0866 0.0 1j0 .-14963 3.191) 0 6331" -'0*074

*26*26 21039 -.0 0005 -.2,*4010 3.s52 3 0.824 -0.086

28.28 2,260 -0#041 -2 4987 3 ,7 "a6 1,o2T7 -,0.104

30,00 2,470 --00.79 --3.4951 3,9137 1.477 --0 t17

Figure B.8. Computer Tabulated Force and Moment Data for Missile III

220 Roll, No Fins, Blunt NcLae

66

MISR!I.F X111 ROIL. 45)y NOF XN#p DIAINT HNO - T71/45/NF/PI

RIJN NUHMUR 18 6DATA TAKEN A11M56 06-MAR-RO

CnEFFICIENTS AROIIT T14H BODY AXIS

ALPHA CN CA CY Cm YmCO ROL CO(DEG)

"-0.17 0.242 0.132 -"0072 .04020 04059 -0.002

2#27 0#229 0,136 -0.176 06193 -0.I55 -0,007

4,35 0,285 0.132 "'0#253 04374 -0434" -0.010

6.26 01367 0*&l12 -0.341 01199 "0.029 -0,0t4

80.2 0470 0.02 -0,431 01728 "-0.712 -0.018

10s27 01195 0.130 "'0.)6 0,806 ".876 -00022

p12.08 0.#73w.1 0,127 -.0,737 1.0215 -. 401.1i -000283

13.73 06860 0612.0 -.0iV03 1.143 -1o104 -04034

15s72 3*034 0.096 -1.,110 1*207 -14143 -0.037

17.72 1,243 0,079 -1"342 1.239 -"16166 -0,037

19.73 1.494 0#04P -.14663 1,.281 -.1.248 -0.041.4

22#23 1,889 0o011 -261!M 1#293 -1,072 -0.040

26.23 2o630 -404048 -.3110 1.654 "-.194 .0*089

28.29 3,047 -0.110 -"7,92 1#.926 -1.361 -'0121

30.00 1 "00,144 --31943 2s,0I 68. 4 "-0o130

" Figure B.9. Computer Tabulated Force and Moment Data for Mishile III

456 Roll, No Fins, Blunt Nos*

67

MIStLUF MV, R7l..1 Or NO F.NSP ]L1.IJNT NO;IT .- .V/0/F/EII

RIJN NUJBER Z13 12DATA TAKEN 1414M9 06-HAR-.-0

COrmiFrCXENT0 ADOMIT THE MOPY AXIS

ALPHA CN CA Cy CM YMC) ROL CO'S.' (DEO)

-0-006 0.017 0.01'9 *-O'007 -*-0 *OTO t0.014 '.06009

2,21 01078 0,094 -'.01•. OtV22 00.04 -"0.009

4,36 0.192 0.092 --01016 0.414 0#007 "0.012

"6,3 04264 0,007 -0"0,.a 0 ,5,76 0.007 '"0.015

9.20 0.302 0.092 -0.032 0.000 0.012• '"0.019

10.27 04464 0.07O'4 -.06029 10022 0.011 "-0.021

12.29 00.53 C• 000 -0.043 1.256' 0.019 -0.0023

13.07A 0 1660 0 1011- -0.04M? 13111 0$07.9 --04027S.•

"" MS,79 0,79i 0.407' -"0.060 IVA,?3 04045 "-0.#029

17.72 01916 01060 -"0.07 1,71. 0,046 -"04031

S 194.78 1.040 0.043 -0 .1062 1 30 0.0.01 -0.036

%',

... 29.21 2. o 39 r "0 0, $ DOW, 2.472 -"0#064 "'0,048 '

-•300 0 3 .0711 -0 11506 "'0 036e; 3,3•73 -'0,094 -0,079

S~Figure B.10. Computer Tabulated Force and Moment Data for Missile IV

[.,. ~~0° Roll No Fine. Blunt Nome ":-.

• 68

2.',

MISS~ILE. XIII RCILL 0, NOl FIN~r FOINTFD. NO 11U/0/NF'/F'T

RIJN NUMBE.R IS 16DATA TAKENIAW 3 06-MAR-90

* I FFICC!Xr TS ADI3OT T14F~ ROJD AXIS

ALPHA rCN CA ry CM YMCn Rt)LCO

2420 0 16 11$A 06123 '"0.014 0,2t4 00016 -.06010

4640 0*273 0#119 ...00023 0 4'504 0.009 -0.013

6, '47 01308 0.111. -.0,02 0,7nft 0002.0 -'0,016

9.#27 0*.540 04 1 e ..06021. 1,090 0.023 -0#020

10.27 0 1 605 0,112 -.00020 1.14 02. 0019 --0,024

12.27 048~56 00101 --0#034 14699 04017 -04027

4114s27 Is 051 00099 "0.0#0,9 11.000 0.031 -0.033

16.20 Jo242 0 1 0 W -0.04," 1303 00.030 -0.034

17s74 1,37R 0.066 --0,01( 2 1491 01018 -,0.037

19o84 3 ol.2 06043 2O3 1 9"09 0.030 -0.042

22.24 160M1 0,017 06013i 36263 -'01001 -0.047

24623 2 0 0? " -0.00? 0.0060 3, 04 '-Oo029 -0.005

.. 12 A.I22ý 0 113 Iq -.0,037 -.00.033 36960 0,0311 *-0*01,4

29,29 2 VOR 1 -0*077 -'0.00 4 7. 04131 -04058

30.00 2,700 -010I4 --0 1 ,4 4 156 0 011110 .040199

Figure B.11. Computer iabulated Force and Moment Data for Missile III00 Roll, No Pins, Pointed Nose

69

------ .......

*11

""M ISSXI.F 1,P ROIL 2?,5, NO FINC, PnlhNTrT - TTT/7?,!,/NF/rT

RUN NUtN IS 1?DATA TAKE{N 161414t1 06--MIR,'0O

COF~rXw4.1NT A~DMIT THE~ DOPY AXISALPHA CN CA CY Cm YmCn RI CO(DEQ)

0.27 003,6 0#117 '-04033 04009 04W1 ".0$006

2,22 0 17.2 -*- "0 b I15 0,, "'67 -. 109t -.0,009

4 .6 0,321 0,122 '-0,164 0,'37 "0,194 -0,017

6.13 01419 0.109 -'0.0207 0 796 -"'0290 -04017

8.30 0,662 0,103 --0t.73, 1060 "0,1396 "0021

10,20 04703 0,101 -'0,343 11321 -'0#41 -0.028

12.29 0.*7T 04102 "04470 a.594 '9 0.51 - 06034

13681 1,007 O09f " ? . '3,9A i, R07 -0, 34 '".0.035

16.0V 1*222 0.079 -,0,790 2,049 -,0, ., -0,034

17.77 1.,384 0061. "-06916 2,230 "-0,492 -0,031

20 2r 14602 0,041 '1.,0? 21730 -'0. 64 -0,0,2

-'22624 1. 1 aIi 0.029 -1 697 3 1103 -.00078 -04085

24,19 %,094 0,015 -'.1969 3 4 3 0$07n -0,101

26,22 2360 .-0,016 -'2,440 3,72! 0,315 -0,1,22

2 879 2.•81 -0#0"4 "4.72763 4,0?6 0,509 -0,131

30M00 30049 "0,s.04 '3,40- 4,21M 1.05? -0.1t9

I'I


22* Roll, No Fins, Pointed Nos.

70

mrZsI F TTIP ROLL. 4rTr NO FiNlr POTfINTrr N - ITI/45I/F/t'T

pRIJN NUMJMR Ifl 20

DATA TAKE2N W26,141 06-,tAR-'RO

COFFrICIEHTS APOIOT TI1.F mODY Ax:rI

"ALPHA CN CA r.Y r, , Ym(nO RnL0 O",'.4 (DEO)

-0•26 0.084 0,o14. ? -Ot07 0.003 0,0291 0.005

2.,34 0,171 0.,14t -00.91, 0, 12111 ..0,1 ,l6 ..0.009

S.36S0 0.239 0.s24 7 -0 ,262 0131,9 -0,330 0.012

6.33 0,320 01133 -.0,363 0 , kiln -.0 ) li .0,017

80' 9179 0.432 0.133 -0404 0,n14 "0,776 "0.

9t2 10.o7 01.140 0.1 30 "0, s60 %5 1.004 -"0, 71t? -0.029

• 12 fl 0,737 0O* 126 0 7 97,T 1 4 At 1' "0 -,1,117 -'.0003

.14. o26 0.741 0110 ',X1000 1,292 --1,23? .0,045

A, 16429 1o173 0,0119 -1,269 1•1 406• -1 43J 7 -06053

a 17.7 41.• 1A 4 512' 106- .0 053 "

L.4'

; 224•3 n0126 0102.3 .. . •, 711,• -- 1 %530 "0.0 1 5"

24.17 2.518 0,000 "-?74 , .9 I I A0 .91.91) -0.0,0!0

26o.l1 n,96f 0. 102 -.3. 3 1,.0706 -2, 1.1 0,0052

28,27 3.377 -0.077 '-3.4Fh• 2,n"91 '".734f1 -'0,*063.,i .

"30,00 3.311 0 , *'0132 "93 k 9 2 .720 -.1. ASO 0.066

•; .4


450 Roll, No Fins, Pointed Nose

71

, * *. . ... a. .. . -,* ' " '. ' ~ ... .

MISSILE I, ROLL 0 F'IN 1. BI.IJNT NflnF -. J/0/Fl/DL

RUN NUNI.R 18 27DATA TAKEN 15136t12 07-MAR-0O

CO'FFFICINTR An)IJT TIt• DODY AXIS

V ALPHA CN .A CY CM YMCr RO.0CO(DEB)

-0.04 0.054 0,2.26,9 0.02,7" 0.061 "OtOA6 "09010

,2s, O b 18 0,243 u0)107 -"0,070 0010, -00011 .

"4.36 0.432 00237 -0.23.5 -0*212 04233 "0,O18

6•33 00706 023.2 "'0 1356 --0,373 0.339 *0.023

8916 1 0,16I 06"20 -0367 -0.677 04334 -0,023

10.30 1.800 0.201 -0,377 -1,4123 0.333 -0.024

12,23 2 o46 5 O.282 -.0,3 03 - J*637 0 433 " -. 0,024 f

14.28 3. 116 0.143 "I, 406319 "2.19 t, 321 -0.019

109 3 * W.1 0.209 -0,422 2.o529 04329 .-0.019

19101 4*313 00069 0#4,16 -2,9.14 00313 -0.002

19,92 4o910 0.021 -"0.443 -3.434 0.300 04011

2 6 "N790 -0,0,14 --01407 -4 b001 0,294 0.03024.21 6.470 -0.072 --0,124 -4.44". O.291 0.062

26.*26 7,193 -0,121 -0.*531 "-4.•8 0,.24 0.100

28o73 7.763 -0O# 1 ".3 -. 649 -5.0215 0'331 0.162

30,00 8,196 -.0.175 -0.198 "-4,RO 0,247 0.143

Figure B.14. Computer Tabulated Force and Moment Data for Missile I0* Roll, Fin No. 1, Blunt Nose

72

. -..... -1"

MISSILE I, ROIL 1. 2.r' 1 A II, ,NT 4Ornsr /t2.5/F/Pl

.. IN Nkll I R IS 30DATA TAKEN J5140'52 07.-MAR.-00

C0FFCINT1. ADOUT TIF~ R'ODY eV<ZSALPHA rN CA CY CM Ymrfl ROi 1O

(DEG)

0.44 -0,31fl 0,'47 -0#036 0ARS, 4 ' 0,0'51 -'04006

2.40 -0,070 0113 -"0,191 0.V' 01091 '"0.009

4,2, 0,300 0,13' "0,401 0.036 0t234 "0,014

6 0,694 0,221 0.t06 -01234 0,397 O,011

1342t,6 160,10 06712 ,0 47 F1 -0 ,645 D1492 -00006

10126 1 620 0,176 -"1247 -'0,0?t 0.84R 0.014

16 o,94 3,9,29 004IF --2 491 -24."03 J4630 011.J 17.77 3.909 0.101 "2,,04 -2',105 1. 801 0.234

19.77 4.627 0.0"6 -3+369 -2,874 21 03 0.701

2421 A644 -0 1021 e --4, nJ1 -3,630 714 139 7 0.60.8

26.. . 6,860 -0,076 - 66 -'3.799 01,74 0.774

.27,71w 7,381 -00.04 '-6.233 -3,S73 2.970 0,79P

K. 30.00 7.706 -0,117 7,I16. t '33 69 1 9?9 00581


• .. * , 220 Roll, Fin No. 1, Blunt Nose

7'I

":i7

MISSILE It ROLL. 47, F.TN Is Al.1NJNT i ,- "sr T/Vn/r i/F:L

RIJN INUMDER TI 31DATA TAIKFI 16i00003 07'-MAR'-10

COF0F T8 ADOUT TfI. DODY AXIS'1 ALPHA CN CA cY r.M YMCO ROI. C0

(DEO)

"-"0OF -0.64:# 0.7o2 0.07 0 750 -0#2 "0.0# 0 ,0

2, '17 -.0309 0 .'13 ,,0. 1fl 0 114 -0.006 -0.015

"" 4,3. -0. 10Mr O.n "0 *5.t2 5 0.262 0#244 "02,11

-*29 00364 014,31 "',- 7 "-0,004 0 °,11,l, -0.030

6.,2 . 7,r9 0.203 '.. °09 2 - 0 •1. t1 0.440 -0.019. 10, 7 1,2, •,0 0,,9 , "I ?,- 7171 - 0 bes63, :1 4 67 -,0,039

121P4 3 s'. 0" 06174 -2364- -1 4013 1.544 '-0 052

13 472 li236 011, , '2,7nt -,1,.273 1.R • ,0.060

962 r) ~0 0.126 3 i011 1 713 2 9222 ' 0.04

"17o7i 3,36n 0,09,1 -13.92 --1 ,927 2,444 -0.1.012

"20,77 4 ,9 , 0. f•2 -4.03'14 4.41. 2,930 ,-0,114

2' 1.,26 40794 0.0l1 "'514 7 7' ,710 3,207 0.,127

24 o23 n,773 -0 o OP 6.30 7 *'AM A r 3.422 -0 .132

26 , 15 1 nnn ".0.0. 2 -'7.123 -'3,076 3 .,11. 7 .-0.1.30

"28029 7o31A6 -0,142 "-7no4 '-?, #. 144 3.602 "0. .1I

30,00 31030 -.01209 -* -.557 -3 .10 3.607 ,0.1.2.1


450 Roll, Fin No. 1, Blunt Nose

1.7

.. .. o .....

I,. . - ., . . .-. .•. , ..- . .o,, . ... ... ., .. . . . . . .

MISSILE II, ROI. Or FIN Ar PI.AJNT NOSE -XI/OI/lL

DATA RUN HUMHB.R IS 21

DATA TAKEN 1313.25' 07-MAR-80

COFFF.CUINT3 ADMIiT THI BODY AXIS

"" ALPHA CN .A CY CM YMCO RniflCO;'; (DES)

--- 0*00 -060871 0,229 0,004 sOaOB 0,004 -0,022

•2o8 0,174 ..230 -'04135 -'0#09,41, .10", -0.027

4,31 0,403 0212 1 '0,25. -0,294 0.244 -04.01,

6' #20 0.678 0.203 -0, 3',18 "'0.5 * 03339 -01039

'49.09 1.121 0.092 -00.359 -0.962 0 43"M -060,11

12.*,2 2129n 0.190 -.,0411 -2.087 0 .2.7 -,06014

13.702 2724 01%31 -, t 0,417 "2,s, 01290 -0.005

16. '2,1 3.394 00089 -'0414.4 -3,108 0.294 0,024

18.03 31931 01036 -"00489 -.36,186 0,281 0.041

20,'9 4,639 0,01.4 -0 5006 -4,187 0,216 0,055

"2 , ',!A ,5•269 -'0,017 *"0, 5,3 ,.4,7.1.,' 0.239 0.078

24,24 5,s9n -0,0,12 -0.,583 -5,1 5 00.74 0,11.4

2 6*27 6,428 -0,078 -0,6¶5 -'$ 401 01214 04167

"28,01 6,821 -0,'10 -066513 -5,417 0109 0.194

30 00 7,270 -0,.138 -00682 -,2147 01103 0,224

Figure 1I. Computer Tabulated Force and Moment Data for Missile II

0* Roll, Fin No. 1, Blunt Nome

-9 75

99, .... 99,9.9. ", , -,.9 , . , . . , .• . . , , ., •,,. -•.. .9 9 9 *9 ,9 .. . '.*~ ...., .'-

MISITI.r 22v RO l, T") FTN I F I. UNT WrflC I .T. I .5/FI/PL'

RONR HU UM9rR 115 22DATA TAI(rN 13*477,IO 07-M-AR-80

COIFrV',XINTS AnlUJT THE n0nY AxiSALPHA r.,N CA CY r.,14 YNCO ROI CO

(DE.G)

-0. ,. -'0 .121 0.258 0.071, 0.0n6 '-0.041 -. 0017

2.*7 0.,307 0,24n -'0.1 i --'0,2!50 0.116 0,022

4#2A 0.674 0.23S -0. R! '-0.457P 0+,70 -0.009

6.17 0.. 07, 0,203 .-0 47t -.01910 0. 49 -0.033

8,21 1 409 0.210 -0.*07 '"--120 0,4 620 -'0.0030

10:U 19 8 0.21790 .0,989 -1,4S30 0.964 -0.016 *'1

12 30 !.)".) 0.168 -1 .1,)7 2 , 35,4 1+207 0.0,5

14,19 31,00 0.±41 -"1.67, "'2.841 1.549 t.067 00

15488 3.5r70 0.118 -2.004 ' 2P%8 1 .704 0.131

17.96 1056e 0 , 0 3I4 -240 3 , 1 0.1O1.01 0.130

19.7A 4.614 0.054 -2.796 '-4,110 2,170 0. o345 5

25.7 5, 3 3 0.01.5 -3,4102 -4,743 7.572 0.,18

24.23 !7., 97 1 -0.018 -3,962 -'44889 26664 0 * .63"

24.2 9! 6.466 -0.064 '-4.,78 -4 9,6.1. i. 66 0.84

28408 e800 -0.129 -5.009 '4 t96l 2.661 0.724

30.00 7.146 --0,144 -5.60F -4 642 1,3,2 0.566

Figure B.18. Computer Tabulated Force and Moment Data for Missile II

22o Roll, Fin No. 1, Blunt Nose

76

'- ,.. .... .... ....

MIST7LF 17, ROLL 45, FIN Ip PIUNT N1CiF T I/47I/F1/F.L

RUN NIMBER X8 23D~i)) TAKFN 1:5I7108 07-MAR-80

COFFXrXHT8 ABOUT THE BODY AXIS

ALPHA CN CA CY CM YMCO ROLCO(DRO)

0,29 -0,OA1 0.271 0,040 0,00k 0-401A -0.021

2t34 012.19 0 #20 6 -01221 -0,213 0.234 -0.024

4,46 0,#123 OfP41 -0#S04 -0.4Ro 04501 -0.034

6,37 0#fl46 0,231 -*0031 "'0,07 01010 "'0.040

8#28 1,154 0,219 -'04919 1" 1."?, 0 1 ? -0*044

10429 1,9 019ti0 • 1 t r ,41. 3 1 k ZS9 1,%1,7 --0,048

12,19 26063 0,M4 -1•,:4. "-1 946 4,26 n -0#055

142 14.22 2,10 OP.121 ,1.59S -. $310 1#,416 ,04060

15.81 2,8 sS.P 01 "'7*78- "7205"'1 1.,4n2 -04073

17.78 3.359 0,046 "240,3 "-2,040 1 .64 "-0,072

20,24 4,061 -0,041 -"n.41! "3,236 1,662 -0,098

22.26 4.AS4 ".0,133 -2 OFlol "'3,19 1,709 -0.1t2

24.23 55422 "04.191 -"3 276 "'1*842 1.736 -0#109

26.26 6 104 "'0,144 -"3.#S7 -"4065 1,700 "-0.1,28

- ~ 27.88 A .560 -0#248 -'3167 -4 s112 1,617 -0si35

30.00 7,303 "'0t447 -4.41? -4,191 1.38 '"001,42

Figure B.19. Computer Tabulated Force and Moment Data for Missile II 3450 Roll, Fin No. 1, Blunt Nose

77

........ ..... ......

*: M.ISS.F IyI ROIL. Or FIN As 1I1 NT nSrF ' UT/0/Fl/BL

RUN NUMBER I8 24DATA TAKFN IW71•33 07-MAR-.80

C0FFFXCXENTn ADOUT THR BODY AXIS

ALPHA , N CA CY rCM YmCn RO!.0(DEO) '3

0450 00020 04242 -0000 -"0%009 04007 "-0,014S2.28 0.3,61 0',236 -"0,013 '0 ,291 001 '0.017

4.39 0,70r 0,214 -0.0007 ".0606 0.010 -0.024

!5nO t1035 01206 0.0010 -.0 09 0o027 -0+016I,•

8.27 1 5It")1. 0 1 afil -0.009 -1 454A 04033 -0*0P7

10.26 2b046 04171 -0.014 -. 1 01 oo -0.030

12 #"31 26644 00153 -0*077 -2696 04044 -0,0075-

13. 69 31011 0,133 *"0.,050 --3 107 04M5 -0.031162 3 3*643 0.094 -0.07) "R.8?1 0,090 -0.077

18609 4,112 0,056 -0,076 "4.3:55 0.086 -0.044

20, 34 4,711 00019 -0.073 "-44,9977. 0,072 -0*041 •

30.00 70.0I -0.013 -0.1073 0.095 -0.04024.23 5,902 -0,060 -0.095 -A,279 0.087 -0.037

26.29 6.462 "01096 "0,0c32 -'6,859 0.102 -0,049 i

28.29 A,93t5 -0.120 -0.092 "'7,169 0.089 -0.047 iI

30.00 7,1.80 -0.1.1 -0.107 '"6,93. 0,071. -0.019


0* Roll, Fin No. 1, Blunt Nose

78

3 3 . .. . . . ., . . . . . . . . ..

MI•.II.E III P RO0l 22.,r FIN It PI, IINT NOS -. .1/22.5/F1/PL

'.4.

RIM NUMMR 13, 25 •

DATA TAKFN 14?44134 07-MAR-O0

COFFFICTEI.TS A•BOUT THE RODY AXIS

ALPHA O.N CA CY r.M YMCO ROL.CO(DEG)

""061 0.047 0#251 -0431 04133 -.04014 -0.007

S2,06 00386 01248R -0#138fF "-0* X 0#069 "00011

4#3V 0#774 0.234 -00322 0'0 4 4 0, 1. 37 -0#021

6.44 1.#t36 04217 -0,49l "0.0sO 0.438 -0.027

8.29 1, 534 0.202 -0.676 --1,.311 0,671 -0.031 !0"3~e4

106,1,0 1,99 0.8?7 -0,912 "'1801 0*9,75 -0.036

S11#96 2 + 42!,• 0#166 -1#179 -.24369 1. 4 3120 -0.040I I

M7137 2*860 0.140 I o 45 2 V.t 90 4 1,6,10 -0,020

15,71 37331 0,106 -1,718 -. 40 4,I37 -0#002

18.13 3,930 0,071 -2.086 "-44,156 24328 0.044

" 2 0. * 4.510 0,028 -2.41P -4t721 2,674 0.*Oslo21, s 17 1 0 7 0 0 0 -", "1. - ,2 7 310 3 O 4

24#2P 5 701. -0.001 -3,#243 "*'" 47? 34191 0.19"

26.2S e6 , 94e 4 ) 06000 "-3.*64 1 '-.5. 5A2 3.1tfl 0.149

. 27190 A.?fl6 -0,032 "3.8 ...,1 5, 7.14 3 276 0$112

"30.00 6 7221 -.'0 049 "-4.471 -, b 706 3.647 0.071


*220 Roll, Fin No. 1, Blunt None

79

4 .. . . .. . . . . . . .

4. . 44 4 4 *, 4 * 44 . 4 .. .74 '

' MTBMSSILF ITT7 ROl.!. 45s FIN 1, BILINT N0sr '" I/45/FI/BL

RUN NUMNBER IS 26DATA TAKEN 34?57t04 07-MAR-0O

COEFMICIENTS ABOIJT TIM DODY AXIES

ALPHA CN CA CY ,M YNCO Rnl..CO(DKI3)

00 0,0 0049 0250 "0#047 0,0 " DIPeA04126 -0u.00

*2o27 04.93 0,244 -.0 ,33A --0.146 0*t27 -.04013

4,41 0,606 0*239 -00608 -0,X95 0,390 "'0*021

6.6 3? 0.891 0.222 -'0.090 -"0.693 0.694 "0.024

F-7

""12.00 3.996 0,sV07 -2.017 "'-2075 2,009 -0.034

1307,9 2#3036 0.160 -2,401 -'.11 0W0 2.5199 -0*029

*116429 20, #9 06 0*1J7 --3s020 -. 34271 3,,3 0 7 -0#033

S18.10 .1343 0.097 -'3 466 -"317411 3.796 '0.009

M0.29 3,R77 0,074 -4,024 "-4o.43 4,346 0.003

22623 4,410 01054 -'4.514 "4,906 4.18•3 0.009

24o21 4,989 0.039 -5.152 -5,409 . 29n 0°023

26#26 'IM70 -'0,004 -55 .946 -15.729 9.0811 0.038

298,29 6,22P -0,053 -6.670 -"5,845 6.21P -0#006

30.00 66891 -0.0000 -'7s293 -.6.0096 A 6,430 --04,041]


450 Roll, Fin No. 1. Blunt Nome

80

4 -

MISSILE IvY R0I,.L O FIN it RL.UNT OSE -xwom/

RUN NIJH8tR I, 32DATA TAKEN 09133$02 10--"AR-"10

COEFFIXCENTS ADUtIT THE BODY AXIS

ALPHA CN CA CY CM YHCO RnL CO(DF.0)

-0,04 -0.080 04203 "0,005 0,001 0*006 *"0.011

,2 22 0,278 0.202 0.004 "'0,297. 0,002 -0,014

4,30 0.571 04109 04000 -0.621 0,007 "0.017

6.44 0.94 01173, ."0003 -1.070 0600 "0.*020

8,35 1,233 0.151 3 -0,006 -'1.476 04012 -.0,021

10.49 1,,?7 0,150 -0,014 -,7. *03 4, 0 0.0?,5 *"0.024

0 12.26 2.131 04129 "04024 "-2.,664 002 --0,0#027

13.95 2.530 0,14 -0048 --3,227 0 .#080 -0.027

16,33 3,059 0,0n7 "0.049 "4.0211 0.103 "'0.019

179,. 3. " •0 00061 •-0.034 -"446,15 0.055 "0.032

"19s76 3,825 0.033 "-0,.43 "1,140113 0.074 "'0.028

22.28 4.467 0,006 '-0)066 -"1.976 0.060 --0.003

24o25 5#00 " -0,01 1 *".0n1 -6.61 0.#0109 0.018

26.06 1 * 4 62 -.0030 '0,008 -"7.149 0,041 0,052

"27a76 5,8345 -.0.0 "0. -06160 -7#422 0.063 0.007

"30,00 6.25 " -0,084 -0.130 '7,430 -.0403A 0.1.01 '

"Figure B.21. Computer Tabulated Force and Moment Data for Misuile IV

O Roll, Fin No. 1, Blunt None

81:*

' . * h , * I ' . * * . . * > . * * . * - * .

""",MI H SSIL.E TUr ROLL. 22,•,5 FIN Ir FI. INT N08F - V/,?2,!"/F1/T4L

RUN NUMPER X9 333 DATA TAKFN 09144:28 10-MAR-90

,'.%'

COIFFXCIENTS AROOT THE RODY AXIS

ALPHA ON CA CY Cm YMCO ROLCO

(DEG)

-0,22 0,037 0*1R0 "'0.011 0.13n -0,066 -0.006

2M 0.047' 0,1C "0.132 "'-021t. 0.00 -"0,010

1 4,31 0 659 0.169 -"0,201 "'0s490 0°21T' -06016

6.30 0,951 0.152 -0#422 -0#15 6 0.405 -0.019

8,9 .20 03 0.140 --0 "'0,V.) -.10310 0 .64 6 -0.06023

10.2? 1 667 0.127 "-0,773 -"'•841 0,965 -0,024

S12.30 P. 4A 0.ia "-1,026 "'2.464 1,293 -.060-3

15,90 2o826 00$06 "'1.380 "-7.505 1 093 -04071

18435 3 1367 0 1020 "1 ,6e)7 '4 k 10 2.a3I52 --0*087

20,26 5*042 0,002 "'-.924 "'4.976 2.717 "'0.OSe

22,23 44320 -.'6017 -2.1117 -'56A4 3o096 '-0,077

24,21 4,700 -0,034 -2s427 "6,174 34429 -06101

26s26 1,071 *"0,003 -'21402 -'6,070 3. 26 "0,453

M28O. 1,473 -0.035 -2.600 "6,402 3 o47 -0,s49

30*00 6,936 "0,077 -'2#794 "'6.000 3.7n 4 0.o24

*Figure No. B.24. Computer Tabulated Force and Moment Data for Miosile IV


4,

82

MISRII E IVY ROILL 45ri FXN 1v 1AWINT NOsIr TU/V /F1/BL

RIJN~ NUM~WR T1 34'I i,!DATA TAKEN 09 tn344 I0-.MAR.-80

COEFIENTS ABOUT~ THt DODY AXISALPHA CMN CA CY r, YMCO R01. CO

(DEG)

023 0,0537 04192 --00037 040nnf 00U3 -0.013

263. 01300 0103 -,0.200 .,0.o 01Nn 061110 -.0400

y 4,13 00.03 00174 "'0#48I "O.03W 0.330 "-0.0 0

6426 0,777 0•64 *-0#764 "0b92 0.674 '0.027I

8.22 14023 06J51 -1.017 1.#032 3.020 -0,0%0

S10 *2 3 1 ý344 0113-9.• .-. ,101, 1,490 -.0,*0 32

12.01 1.6AR 0,124 - "1$606 - 6 #964 -0.047

013*16 2,037 0:104 -.21031 -2 6 o7 2 1 .455! 1 # 75 2 # eo 0 #0 7.) "' 366 --3,077 3o026 -04044

•;i18 033 2MA O0042 "'2,X "'IA -3 o73L 3 * 97 "-00 030

20*23 3.*43 4,0 1 -3o91 -4.211 4,207 -0,026

22.21 11592 '0,000 --3.651 -4,771 4.0-7 -'0,018

1*24o23 S 09S -0.038 --4,033 -- 5 222, 5 .3 :1,2 -0.0407

26.26 4on"9 -.0,030 "'4#411 -'646 7 1. 6 0.002

27.98 4.490 -0.036 -4.695 "o.7s11 !rj3 "'.0t,6

30'.00 4,767 -0.0405 -".003 "5.734 5,.1. 9 -"0.094

Figure No. B.25. Computer Tabulated Force and Moment Data for Missile IV

• •.. 450 Roll, Fin No. 1, Blunt Nose

1I 83

I I II I II I1

MISSILF T TI ROLL 0 F XN PO TNTr. NO•F " .T,/O/F.1./FT

RUN NtIU•ER 71 40DATA TAKFN 11:10141 10-.MAR-.O

COF.FXCTFNT3 APOUT TIF, DODY AXISALPHA CN CA ,Y r. YMCO ROtLCO

(DEG)

-0,05 -0,0, 4 0,'26 -06016 OiOn4I 0,027 -0,009

2*12 0,374 0,211 -'0.017 --0,26i 0,02"1 "0,017

4.3 0 0,776 0#707 -"0011 -0600 04040 -0.,04

6607 1,127 0b195 -0.02 4 "'0.947 010,111 '"0,026

8,32 1.637 0.,176 "'0.03r A ', 479 0003" -"0031

10,29 2. o1 "I 4 01 0 -.'l.¢q "0,030 "' 111t 000•1t . "0,037

12,28 2,72 0,A 43 -'0033 "'2,630 0,043 -'06046

13.74 3,114 0,.128 "0.04t -.3@040 0,06" -0.034

15,74 3.6O1 0.092 -0,06: -3.M73 0,083 -0.0#98

17,77 4.1.8 0.054 -0.0"7 -4,1'11 0,141 -0.072

19.73 4,668 0.021 -'0.057 -4o648 0094 -0,097

22.26 1*391 -0.027 -0,040 -.S'316t 0.24A -0.144

24.20 5.984 -0.070 -"0631 -).941 0.:93 -0.1931

26.#3 6. , ;65 -0#106 "0,064 "'6,41 0.231 *-0,.t7

27,71 60929 -0,124 -0.0R1 -6$643 012:26 -0.1.47

30.00 7.268 -0. 11,±9 -0 11. "-,297 0,171 -0.088

ŽFigure B.26. Computer Tabulated Force and Moment Data for Missile III

0* Roll, Fin No. 1, Pointed Nome

81 4". ,1 '• " . . * • • • • .• • 4 ' • " . • . • • • • • . , .' ' . , • " , . , , , ' . . . . , • , , . . ' • % • % • , . . . , . . - . • , , ,' , . , •

MISSIVE XY.1' ROI.. ýP5 FIN I Y PrnXTFri N X.T.III*,'1 .!/FJ ,F'T

RUN NUMBER IS 4 1DATA TAKEN 11I8t!"2 1.0-MAR-80

COERFFCIENTS WWOJT THR Wfl'lY 6UIS

ALPHA CN CA CY CM Y1C`0 ROL. r

(DEG)

"-02•A 0o101 0o210 -0.047 041,i -0,040 04000

2•17 0,480 0,112 -0.204 ".01,30 0,092 -0.007

4.3A 060t3. 0$193 -0 '365 -0,497 0. j, -06.025

6o,7 1 41R) 0.171 .1,111 "0 0 0,43R -0,024

7o1 *#4¶' 0,162 -.0169"? "1..1 flo 04A33 -0402$5

10." . 01.2 00.49 -.0,949 "1 , 0? 0 976 -0,040

12.00 P4o 0#171 "--262 "2,301 1129) "0,049S14*20 30028 '0,099 ..1,• 4M 2,# 71 1ý69? -.0,036

16,29 3, 44 0.066 -j. Ra "N.330 2007 -0 "'0.42

17,99 3.940 01039 12 170 --3 ,792 2.267 06006

"4,2 O 4*420 0,036 -:1, #"2.4?4 1 4,7281 2. r, 0.t,24

24,1R 5 o617 -0,046 -.711 !5 1041 1 0 ,4

26,.23 6,01.4 -- 0 .0 V' -*773 .. 1 730 3.467 0.078

2.a29 A1,5 1 -0.071 -1.070 -4 .37 3,5T7 -0.077

30,00 61,51 "0,075 ,4141 -"4,C73 1 3,SS7 '-0.0777

V.7

.'4 Figure B.27. Computer Tabulated Force and Moment Data for Missile III

22* Roll, Fin No. 1, Pointed Nose

85

HISSTLF TI, Rn.I. 15v FIN Ii POINTrT' NOS - .II/4•/Fi/F'T I

"U"

RUN NUJMCFR TS' 42DATA TAKFN 1.4:271.1.7 10-*AR-.O,0

COF.FFICUENTS ABOUT TIHIF. SODY AXI3SALPHA CN CY flM YMCO RMI (.O

(DEB)

-0,09 06047 0,20e *-.067 0.141 0 0, 1 1 0.00002 43 2 0 0 3 616, 0 62 0 7 "'0 ,3 7 0 - '0 .1 3 0 .." I'"IO o i 0 ,0 0 7 ,,,

4.54 0. 66W) 0.19 "0.679 -0.412 00 42 "'0.012 V.

•; 614e 0193. 0" .. 00 0 -0.#674 0,702 .001-8at O 26' 1,772? 01 •1,64 " 1. o 25 7 "-1 ,036 :1,07T -'0 #0,24 -

10.2 1t~ 1 6,30l 0, 4.1t~ -1'%5,/7(q "'), 2. "o I1 ,1517 ,1, -06030

1M.29 2407T 0.12 '2.301 T. P 'Z,0 2+1109 -0.03713.96 2 ý467 0 ,1,• "-21,17 1. --2 , 4A3 24."0M• -00033

16.00 36041 0,075 "'3. 16! -".007 3,137 -0.049

18010 31,:1,6 0,077 -"', 65 7 3'3,4 5 ,130 1"0.037

19.77 36920 0034 -4.067 -'3.709 3.173 -*0.04322,21 41609 0.02 O, "4 ,FO2 -"'4, 02. 4.5 4 1 '04061 ••

24M.I 5 .23 -0*013 -F1460 -'-,159' 4,82ri -0,0I8

26.n3 -.99 0.037) -. 6,In? -.1,909 P. t r 11-06081

27,79 6.4A -0.0 00 -6.7O73 -5 4.07,) ,p 403 -0.001

30.00 7,13 -0,107 -'7 olI1r --'5 6271. ro. 10V -0,09

Figure B.28. Computer Tabulated Force and Moment Data for Missile III453 Roll, Fin No. 1, Pointed Nome

86

.1t

4. U' '4 '. *. ''Is

MISFIIEF TII, ROLL Or FIN 2y FKHUNT NO, . "X./O/F2/PL

RUN NUMtJHR In 43DATA TAIKFN 1*:,13n2 I O"MAK"'80

COEFFICIENTR AJOUT T14F DOTPY AXIS

ALPHA CN CA MY rM YMCO RntIo(DEG)

-0.09 -0.1.4 0,272 0.001. 0,096 0.012 -0.015

S2.12 0 .330 0,2711 0.009 -*0. 45t0 0.02 *"0019

4s28 04776 0'..251 .06002 -0.90 M 0.01? -01022

-60 1 1•11101 0 b23n "'-0,014 "'1b536 0.033 -0025

a.PH 1.711 0 02 2 11 "0,01"? -2.1 R6 0 10 1)0 -0 - 12

I.10 25 2,14S 0 62041 -.0,03 --2.2717 0#00n -0.041

O 12#30 20809 0478 "0,049 "'3,'4 00.091 -04042

13473 311911 0 1 115 0 0 621 -. 41131 0*091 0.038

15.84 3.719 0.109 "-0067 "4 #79, 0 00R,• " -0•033

18.01 4 , 211 0#037 -. ,0114 1.,4 4.9 0.090 '"06038

20,15 4.779 0.023 -0.077 -6.038 0.1,1 -0.046

22.2,,' 51.317 -0,01,8 -06089 A , 164 0.14 -0.045

24,20 56812 -0.001 -0.085, -7406F 00144 -0.0r)2

26o26 43 41 -'0.,101 -0 ,12.7 -'7,1.44 0.18%4 -0,057

28.08 6.671 -032r -0.119 -7,744 0.190 -0.093,. 30.00 7#091 -0,144 -'0.0100 '7 ,871 06.08 -"0 134


.O Roll, Fin No. 2, Blunt None

87

* '..A, A A,'-,,A L ,. ... A., %....:• ',• .• A,'-' .,J+ .• *., ' " " '•' % +-"-" + " * +" ' " - . .4. " .,

MISSLF 111p WI ROLL 22,' FXN y FLLINT NflR "1X/2 ,/2/PL-I.,

RIJN NIJIMSR IS 44DATA TAKIFN 1314013 10-IAR-S0

COEFFICTENT AD•IOT TIM• MOPY AXIS

ALPHA CN CA CY ,m YNCO ROLCO(D60)

"-0.10 -0"040 00266 0.030 00115 -q "061 -0.008

4,36 06703 0.4213 -.00309 -".997 0,300 "0.0111

8424 14604 O.214 "0#720 "1.900 0.972 -0.030

11.88 26503 0.24 37 --1.212 --36211 1 #606 --0.043

14s27 3,080 0616 -1"51,0 -'-3?,4 ,111a -"0034

'S,16 437 3 * 561 0.200 .1.9 20 - 4 #137 2,413 -0.037

M20.0 4,407 0.030 '2 ,406 "5).433 3.160 -0.100

22s25 4 1OR 0.1010.0 "2630 "-.5,909 3.392 -04202

24,18 p,389 -00030 -2*940 -. 4316 3,401 -0#249

24.27 1,444 '-0#074 -. #3 6o81 3 ,4 30 -00.269

21.30 6.350 -0,077 '".*19p -'7,192 3.3V9 -0.292

30M00 6171R ....0,094 -3,947 -7,260 3.,11. -04139


22' Roll, Fin No. 2, Blunt Nose

-8I

M ISS EI TI, RtI F T ROLL 17 F 1 % 7; 4I, UNT N'FTS. , ,T 'A!

ROi N H10 ,R ,S 435D1ATA~ TAKE.N 14'S*9 1.-IRP

COSF.FI'INT, ASOOT TH, IPOT'Y A:;'IS

A ALPHA rN CA CY rM YMWf R0l CO~44.4(DEG)""0,,;0,35 0O, OOF1 0 , P77 0,011, " 0 , 0, 12 0,01. -, 04009

2 22, 0019 0*27 0, 25& "' ,4• ..'0' 1 ? 0 6" , l -0'0 13;

'~6 t. 6 40 Otn "$ 0,240 "'0, 36,8F ,, .,. '1 0 1, t,, I" • 02U•

:•'!8,16 1 02 20 O M162 0 6•f -1 ,,O e) 0,'w 1 607, -0.02S•' 4

N12,Z27 2 079 0 1 1 11 '0 7"o lo' 213 -0 0 07J3

16,41 2,897 0,133 2 1, F) * A• 940 -0,0''-17o90 O 313, 0 04,k04 -'3,340 -1'4 798 4 .,11 "0,015

19 5 34,7 N 0 077,- 3 776 -4 RRIP I 48A 1 "0 .1

" 2 , ," ,23 4 , 7..1? 0 019I -'4 o471 -5 66,) ) r,"70 0,000

24,21 4,99.1 Mon 071 674 21 AJ , .1 i ,0 01,,6

26,2A IN, 064 1 .0,034 .•,7) 75 ".6 l002 )1 1 11 9 0.098

28 .170 6*02.19 -0 $069 e, ' .5"1 MJ.F e. . or 0 1092'••"30.o0 A , 110 R .-0 11I.3 -. 7 040 -7,3006 7,10. 0 ,027

Figure B.31. Computer Tabulated Force and Moment Data for Missile III456 Roll, Fin No. 2, Blunt Nose

* • ,'- . ~.''l,,,,. , . .. .. 4 .. " A w '.. • 4 ,•, ,• - - • . - •' " - " " ' ' ' " ' , • ' " , " • - t .4. 4, ,. ,". , , . , . , . . , . . . . . , , , , o , • , , . , , , , . - . • • , . ; • . , ._ •• , , .

MISSILE .TIP ROLl. Or FT I 2, FO.1NTFT.1 NOSE. "' .T/O/F./F'T

RUN NtIM..R .T 46 46DATA TMIKFN 11:1 8:6 1 0fMAR-oji

COEFFICIENTS AOIJT THE qOf'1 l ISy

ALPHA (N CA r Y rCM YmrO R01.tO(DEEG)

S-0.18 -0.11.9 0,771 01000 0 , 00,5 0,011 -01015

0.?2,28 0,3r7 01,.62 01 .006 -.0 46flF 0.011. -0.020

4.37 0,757 , :1. 0.004 -1,007 0,01n -0.002

6,37 1.,04 01228 -'0,00.1 -1 115 0.0'7 -0,026

a.9 O'.~'3 -0.011 -2,139 O.0n6 -0.034

10.2,7 ' , 4•41 0, 192 -01021 "'4 .87 4 0.0n9 -0.,0',o

12 s2 24o06 0011A6 -0,029 -3 576 0#094 -0.O * r.

14,27 4.339 0.124 -"0 011 -"'2.11,8 ot0l -0.051

16,30 76R38 O.OR2 -0.044 -4,81. 0.090 -0.044

"17.80 41079 0.048 "0,0,4 ,.•66 0 ,131 -04,063

20430 4.S?1 0,007 -0,017 -",8,7 0, 113 -010OW21o2• , 4 • 04 -0, 031. -0 ,0 0!'o -. 3.5 0.1 1 ri 1 -0,11 t I

24,P0 5.t17 -0,069 -0,001 -6.7?5 0,167 -0,141.

28 .1 6 1 712 0 -0.170 -0.007 -7P.43 0, ,IN1 -0,070

30.00 70101 -0.143 -0,119 -.7.R 0,204 -0.OB1


00 Roll, Fin No. 2, Pointed Nose

90

., v•,..•l~~~~~w•,w'••... .%•••. .•... •... . .. .N .u.'.......,... . ,....... .... .. ,-.

MISBJI. F rITT RnI1. 22,for FIN 2, FPOINTEDg 1 - I1I/22..IF2/F'T

RUN UJMRR Zfl 47DATA Thl(FN 15101:31 10-MAR".8O

COEFFICIENTS A•UT'THR BODY AXIS

ALPHA ON CA CY Cm YmCO ROLCO*.11 (DEO)

" -0.04 -00,14 0,.60 0,047 0000 "'0,60r2 -0#005

2.39 0,403 01242 ,-0,18 *,0,441 0. 1 -0.010

6#27 11164 00.26 -0,494 -'1,37.1 0462" "0s022

7.84 Is48 0#202 "..0AM -14830 080h -0,026

10.28 2.097 t 182 -"0,976 -*1*A. 9 1.365 -0,048

.012#30 26.01,3 0.0 , *"w -I o266 -3#234 30364 -0#.01214#24 3*09.1 0,123 0t "' 11, --3,793• 2 s06 -"0#041

:2 16,29 3,596 06090 "-1.34 -40345 2,404 -0,051

17.72 3*,84 0,070 -2,0s3 "'4 6s2 "711 --0,062

S20428 4#462 0°028 -2#464 -#,214 3,176 -0,109

M2223 41942 -0,004 -"'177• "'-,647 3,42 "-0,174

24.#3 5509 -0043 "'2699A -6.03,' 3s.79 -0,284

S24,26 A6407 -0,077• 3.1fl¶ -."6 349 3,340 -0,348

'a, 28s29 6,s380 -009" "3,sr17 -6,636 31"9 -04366

30.00 AIM2 .0s113 *3.Is32 'A 1. 6 .34566 "-0s431

Figure B.33. Computer Tabulated Force and Moment Data for Miasile III

., ,,,~, 22* Roll, Fin No. 2, Pointed Noma

91

MISSIIIF , ROlI I. 1ýI; FYN r F'O POINTED OF - TT./4/F2/PT~.e

S.

q~~ RUNf MtiMSF: L 48DATA TAKF'N 11U1rl1 -11AR

E POFICII.TS hDOIUT TR,, "TiOTY A.XTi'

ALPHA rN ,A CY rM. Y-rl ROL. rO

"-O."I -0.071 0o1419 0# I 10 04 0781 "'0 ."0.Or

2.24 0.7!9S 0. 47 -,•7 . .0.0012

4. 7 ,1003 0,OP9 -0.,!"49 -'0, 0i07 , 61± -0.017

6130 '.030 -0.210 -,,00 ., 097 1. '033 -00023

i El1%'

8,2 1 I3 0 s2 10 - , 7 o - , 2

10,urs 1 5.011 -1A2 -24. Copue T4uae 2oc tn Moe6 Dat fo0M904e 1

•;,16'n9 20.980 0.30 10, - 039 -", 6,596 '3,77T -0.0,99

,17 ,719 • 3 112. 6 0,077) ...,-3 19r -1 " 0 ? 17, t?A• -0.038

S20.30 1 ,9 AP 0 , 0',10 ---1 11t 4 --1 73B 4, 97o7 - 0, 0".44

2n• 2 5. , 4., 3 3 -.0.008 ..4 68 1 --,S 1,• 9.40,7 -0.022 •

.. _24 1, .t F, 4.1 A1 -0.04n"t ,.)•. 30T ...5, ? 1.? ,T 7 8 '1"1 -0,1:13

:•266,1 Pi S , 1.4 '-0 ,0F4 "-7, 96? ''A 0,90 6• 1 1:1', -0 03",

30,00 110010 - 1. 0 0l -.7, 1.40 -.6 '309 ,• 4%0 . 0 A 1 ~

F~igure B.34. Computer Tabulated Force and Moment Data for Misiele 1Il

45' Roll, Fin No. 2. Pointed Noser

92

S S.•

MZ8RII.,F TTI ROII Or FIN 3r KIIIHT NOSI - .Tt/OF3/T.L

o,,

RUNl NIJHEr•R IS 51DATA TI•RF.I .16,:1.1:.•18 .10- AR'-8

COEFF.ICUENTR AP•OUT THE MYJ' AXtIS

ALPHA CN r.,A CY r.H YMCO Ra~ot,.(DEO)

0.25 -0,02A 0,6763 0001, 0.006 ".0100t -0,015

2,,30 01331 0,244 01010 -0.0197 01001 -0.017

4.17 0*?•0 0.47. 0.00 -0.*497 0.000 -0,02.1

6.33 1. 206 0.230 -01011 ."00001 0, O009 -0.024

;8.33 1,704 0.227 "0.003 -".- 314 0012 -.1000283

1001 . 21,69 0,220 "--01. 741.4 0,030 "0,032

12.49 2.9,!; 0.201 -020,7 "'2,676. 0,02, -0 030 -

13167 00186 -0,037' .3.031 01010 -0,033

15.95 4.070 0 113F ) 0.0639 -.3.8$4 0,034 -0.016

19180 4,719 0,119 -0.0, "-4 * ,13t 0.044 -0.0315

20.P4 5. 4N .0000l 02 -!'1Q. 26 6 0,079 -0.032

"" 2.24 6. 117 00,3 -0.087 -,9,#9 0t106 .06038

24.19 6. 4 ?7 0.010 - 0.09F) -.A. 706 0, 01 - 07r,-

264 o 1 7,.511 "0.03 "01092 -7.,400 0,036 -0,049

28,29 8.067 -0.037 -0#147 --7.v"96 0.194 -0.06,5

30.00 M 6003 -0.017 -0., 176 .7.964 06.137 -0.036

,'q Figure B,35, Computer Tabulated Force and Moment Data for Misuile III

0* Roll, Fin No. 3, Blunt Nome

" 44 .9

M19SS..F X~l R111.. 73#5 FIN 39 FII.IJT Nfis -4,,

RON NIINAR XR .2DATA TAKEN 16127?11 "0-.MAR-8 .0

COEFFICIENTS ABOUT TIHE DnOY AXIS

ALPHA CN CA CY Cm YMCO ROLCO(DEO)

"-0,21 -0405 0,241 0,040 0.109 -0,0.0 -0,021

2*23 0 1.356 0,249 --0 , I4A '0 .1 0 0.00, -0.014

4.30 0,744 0*1.' -"0,323 -0.911T 0.100 -"0#1 OI

5670 10018 0.229 -'0,436 '.O4W 00.329 -0.025

10.21 21,69 0$199 -1,063 1 t7?9 1*039 .00*044

12,49 2,709 0.273 *.,.435 -2,107 1,474 -06073

14.-29 31387 06147 --1177t -.3,100 1194R~ 0.009

15,92 3OP61, 0.123 -. 4059 -30696 2 3.10, 00034

17.72 4,M73 0.094 "'2.9 "4,2 # 2.5 04069

19t73 ,0o 0,067 --.29R7 -40950 2,973 0.146

22#25 5 91 00038 *3.369.1 -9.1 3 #130 0.'.69

24.18 6,471 0.010 -'3,722 -6,147 3,477 0#320

26.2& 7,101 -001?9 -'4.124 A 113 3.4 ,1 0.338

28.04 7 91 -06037 --4,461 -. 479 3 6751 007

30.00 8 273 --0 0112 -'4,944 -'7,113 3,817 0 t1102

Figure B.36. Computer Tabulated Force and Moment Data for Miauile III

221 Roll, ?in No. 3L Blunt Noae

94

.............. ,...,...... ............ .

MISS11IF YITI ROlLL. 17); F147W 3r 4INT NfPF Tun/iP

RUN NRIM IWR TS 13DATA TAKri4 07?56VI*1 I.1.IARS

COEFFICIENTS ADnUT THtE RnIY AxisALPHA CH rA CY Cr YMCO RfLA.O

(DEG)

0.12 -0.01R 0. 6 001.7 0,021 0"0,25 -0#014

2.10 0. ,5 1910 --0, 1714 1.2 n Il 0,017

4o22 01522 00243 *001,0 -0,73 0436A -0.0010

6,37 ,O.R6 0,23A -0,070 -00.6R1 0oA76 '0*020

Ss17 14216 001•.2 ' -- I21 "'1042 14050 -"0.073

12o2. 2 24279 DORR P1 *2,29, -2 , $4 F) 24p -0.037

0 1i.t 1,774 0,179 "1,79 "8217 2,03 -0,022

:":' RO 31813 0 .114 ?) 90 -"4.017 3.94 -0.014

19, . 4*'16 0*097 "4,9U4 -4,520 4,4T0 -0,00n

216.17 3.1 16 00062 -3,(3 40.'0I 11 03 6 0.036

24, 21 5,84 0.042• -60042 -A.0QT 6,027 0,077

S2.2A 6,713 0,00? -619214 -A.771. 617.19 0.070

2 28.20 7,411 -0,02F) -7.692 .- 7,260 7-247 04100

30,00 b2,71d -0.053 8.",491 -7,173 7,703 0,037

Figure B.37. Computer Tabulated Force and Moment Data for Missile Ill

45' Roll, Fin No. 3, Blunt Nose

954 '. . . . . . . . . . . .

MISSIi.F. .II, ROI. 0, FIN 3. Pl I NTFT.,I •F -' F 7 IT/O/F,7/F'T

.. RUN HUJMBIER .S 54DATA TIUFN 0FVi'$234 A .1.-.M6R-FIO

COEFFICIENTS hPOUT T1F BnOJY AXIS

ALPHA ,N CA fY Cr YWCO; ROLCO(DRO)

0,20 -0#074 00,1.9 0.014 0 q.0ARF "(',00r -0,0142o 1.3 0 1 10 12 0 ,241 0 16. -"0 101 04000 "-00017

4,45 0.739 0,2.1 0.011 "'0,911 "0.006 -0,0o4 "'

6.31 1..140 0 1 i 1201 OoO.4 "0,1146 '"),001 -0.026

s.lo 10636 0,2•1 0,000 .. 1A 2B4 04004 -0#010

10, J.21 2,, 2, 4 04209 -.01013 .,,1, 17001 00011' .06035

12*27 P, o907 0,388 -OO !1O-IR•1i0 O 0 "? -0 003Sl...

13 . 7* :1 ,40'1 0 :,178I -0 , 0, ,14 -,3. 0 73 0 0,164 -0.045 :

164,!IN: 40,34 0 6 (1 ro -010,72 - 1O4 M04 0(404 -0.oP.0•0

19118 , 1 . 714 0.112 -01040 , 138?: 0.071 -0.065

19,7.1 E.92 0408A -06041. A4, , Rreq 0.1d0 -0,081

42,2#V. 8 A.1, IA4 0,04.) --0~ -- P 1 0 , 7 -0# 126

24 s:2 A,894 0.000 -0 4 O4 -'6 s434 0 2.21 11 -0 1 1. !

25o77 7,496 -0.036 -0, 061. 0,.J. 9' -"00.,i

27. Sr) 8 t, 0 14 -004W -'0,071 -'.1•1 0,307 -0,,1.9

30.00 S o 6 4 -0.076 ,0. 16? 7. 444 0 P 7 7 -00104

Figure B.38. Computer Tabulated Force and Moment Data for Mismile III

00 Roll, Fin No. 3, Pointed No*e

96

MISSIlF XIYROI.L d!-)r FI1 3r r3y'INTFTi NO T-T/•.,r/iPT

RUN MUNRCR IS )3DATA TAKEN 0R825*27 11- MAR-,0

*1l

COEFFICIENTS AWLIT THE S0D AXIS

ALPHA N C A C Y C YMC1 ROL CO'2 (DEG)

0.02 -0.0I 0.239 0.0-4 0.074 "0,037 -0#014

I"2*26 0.348 0,242 -0,129 -0,.147 0.053 -01016

4s37 00689 0.22? -.00301 -0.400 0,i590 -0*072

6920 1,120 01224 "-0.00 "-0,769 00389 -00031

84.10 16508 0.201 --0,727 "-1,175i 0.631 -0.040

10*27 26174 04,91 --1 $059 -1",76 1.034 "0,049

012.30 2.792 0.0165 -1.418 -2.437 1.433 -0003314,10 3,167 0.141 --1 762 "3,042 14804 '-00003

16.07 3.932 0,120 "'-%113 "3,60 2,I.)2 0,040

IR.37 4CA70 01082 -'2,571 "4,260 2.o67 0.099

20*05 5,1194 01066 -"2,941 -4s.707 2s847 0.162

24. 2 6,601 0,003 "'3,55 -9s792 3,fl9 042•0

26.23 7.132 -"0t004 -42292 "'6P 02 3,703 0,325

M1 29,13 7.770 --0038 "'4.77" -6.A15A 34974 0.315

30,00 8.424 '"0,084 -'5l.103 "-63,17 3,973 0.327

Figure B,39. Computer Tabulated Force and Moment Data for Missile III

* 22' Roll, Fin No. 3, Pointed Nose

97

"MI,•SILE ITT? ROU.I. 41,v FIN 3p POINTED N08 - 1X./45/F3/PT

II

RIJN NUMBEFR 13 56DATA TAKEN ORI,37T,0 11-'MMR-90

C0EFFICIENT AR0IIT THE ROPY AXZ8

ALPHA rN CA r. Y CM YmCr ROLCO(DEO)

"-0,19 -04030 0,249 0*074 0.090 -.04100 -'0,013

2,11 0ob29i4 0.249 "062,16 "'0.10.12 0.01 -0.017_,..

"3.88 0950" 0.236 "0.4 7!7 -0.279 0.-,10 0.022

6.30 0924 0,219 "0$90,q "0,64!1 0.410 "0,028

8.26 10207 0.207 *1.2oM -04997 1.007 -0*01M

10,30 1,773 0.189 ".1,731 -- 1,937 1,t79 -0,039

12.26 2.3436 0.173 -"2 .3•IM -"2,145 2,100 -0.045

14,#27 2,#74 061453 ".2 91.1 -2, 70 2$,11"8 -0063

"" 160.22 3.3NA 0.140 "-,447 -36.197 3.*24 -0.066

17,71 3,793 ()#%On -. 31867 -3,1,79 3,421 -0,067

,;19,04 4o419 0,082 -,414tl --4 , V! 4 1 :1.• -0,070

- 22s27 5 s 29R5 0,01A ".503,19 "4,77A 4,7063 -0069

24o23 A.107 0.034 -"6IA14 "'1,.243 5) 4V64 -0.098

24,23 6 1 862 06004 .-A 9,13 "-.61.77 !5s441 "00089

28.,4 74609 -0,026 -7,4683 " 118 0'I -0,096

30,00 00.590 -0 •4.1 "-,1o70, "-.6,230 A.173 "0#145

44 6

Fisure B.40. Computer Tabulated Force and Moment Data for Missile III450 Roll, Fin No. 3, Pointed Nome

" 98 98

44 . . . 44.. . . . . . . . . . . . . . . . . . . . . .

M ISI F T,Rl I. 12,?1 N0 F PXNI. UNT N0CE - I/11/NF/PL

RUN NIIHJRR il 1L DATA TAKEN 36122139 13-.IAN-02

cnEFFICENT3 ABOUIT THE WIND AX1IALPHA CI. CQ i cc CM rH rNCI.W

(DEO)

041A -0,002 0,1438 -04020 '-04031 0,021 04021

2.10 00100 0,111. "-0,023 01271 0,013 0,015

4.10 0,23 0,1A45 "0#044 01563 0.011 00015

6.10 0.403 0.190fl "'0072 0,0171 0,010 0,033

7,97 0.599 0, 22TO "0200 12,20 -"06005 0#046

9.90 01030 0.2n49 ".0617A 1.66 0,019 0.093

11,92 $,08. 0,3672 "00279 1,931 0,045 0.207

13,o 7 16391 O.45fll "O.40A6 2,.43 OOn6 0,304

17.91 1,917 0,7290 "06fl39 21935 0,376 0.tll

19.97 2.,04 0,90?77 -'Aji 3,241 046'. 1,237

21.034 7.4110 161140 "151 30,36 019611 1.4

23.95 7,047 J,37$4 ".959 .01 6 1.377 1.862

26.31 3,N04 1,6 65 "2,493 4b253 11810 2.031

27,98 .79 F1003 1,9239 ",2#702 44447 149TTo 1,924

29.70 4,19n 212394 "'3$099 4,594 1,9I42 16A43


III Roll, No Fin, Blunt Nose

99

MISIL.E yRnlI.L. 33,75VNO FINsTI.UNT NOflr S/33/NF/L

4,'.

a''

RUN NU!HDCR I. 2DATA TAKEN 0Ml13!56 14"-JAN"-S"

COFFFTCUNTI. ATnfltT THF WTND AXIS

ALPHA rL CD CC CM rNW CLW(D90)

-0.36 0.00, 0,1364 -0#004 -01096 0000" 0,006

2,01 0,t46 0,14n7 -'0,016 0-231 -.0,001 -0.001

4,10 0*2114 0,1736 -0,04 0.541 04001 0*003

5*99 0,i47 0,2067 -'0,0 "25 0130 01001 0,004

7,99 0,700 0.2471 ".0,0.13 1,168 04004 0,006 I963 0,976 0131*57 .010fl3 1,471 00016 0,031 -1

11,72 ,3*39 0,4239 -0,137 1,739 0,0.110 0,083

M.774 t74 0b5626 ".06201 1,770 00093 0,144 1157 21. 0129 0.4735 -0.#2379 2.200 04038 0.0,23

17,96 2. 787 0 ,97k13 "-0 ý427 2 477 0 6 96 0,422

J.9490 1.4262 1,7367 .04,166 2,740 04,•79 O,4 O

2t*9 3#0 1 f57fl --0.747 311011051 5

23,98 44476 1,9542 --0,917 3.462 07,70 0*778

2r),,04n 0 l 2,3689 ".195 3,*173 0,949 0.902

27.699 le !F 2.8201 *i44't 4 4 2 9 " 1 ,2 tt 058

29,72 61003 3 t"3 1 (. -1. 720 4 0491 I'.589 1,030

Figure B.42. Computer Tabulated Force and Moment Data for Missile I330 Roll, No Fin, Blunt Nose

too

M 1 qS lI E I T PR Ol... .1-1 ?.r~ N O F X1i P-I.1)1T INO SF .- .TT/ .1.1./1. F'/ T!L ..

RUN NtIUMSCR 11 3

DATA TAKFN .5, f4tI?24 .7-,IA .-82

coErrrciT.UTS oPOT THE wi,1. AXIS

ALPHA C1 rT1 rC CM CNW CL.W*(DFOg) ,

0413.,01 011364 '-0,004 0,002 41. 0.0401t

2,01 0,08 0 1,471, 0"010S2 0, 267 01001 04003t,-

4,151 0,17 0 .6 -0 , 00" . 0 0 "Ps "4,04, 00r -,03.00!

6,03 0,.10 0.t700 -'0.0003 Q,?RO Q,40100, ".0003

7409 0944S 4, 030 -04030 1,390 04001 .,O1l

9.rl7 0,M94 0,2361. .. 0.011 1 1511 0101.3 0.028

I• I 1,9A 0 , MP 0 11939 -. 4 160 1 1.3o , 04,044 0.112_•

341 0,97n 0 -0, 257 2 17n 01.170 0*187

1.5491 10 :182 0.44, t4 -01.76 7 OR 4117 4..43 21

17 ,92, .16,1.11.1 0 '390 - 0 . 6 0 .081.1 0.3 2' 0. 4181

20t0l I.,599 0 "0,790 ",A I 0 .r5r7 0.878

21 1 , ,.A I MA 0,79,36 ".1009 3 4 1.5 0 S1, 1 ,1 .17-23,66t P.149 0.9470 1-, 70 6 ,• 1.460S .1,1 106 .1., 47 A

29,6 1 2.44 41 1,t377 1. 703 1,765 6 1 tl 1 .,6 4 7

29 o0 7b792 1.3149 2.O419 3,097 1 b1303 165

Figure B.43. Computer Tabulated Force and Moment Data for Missile II

1,, Roll, No Fin, Blunt Nose

101. . .- . - v

• ,,..... ... ... 4 . . .. . '. . . . .44

M I SSIF rT I ROI.t 33.7-77Nn rxNrF.:L.U NT NO SF 1/73/NFP/~L

RUIN NJMPE.R TI 4DATA TAKFN 1.102$12 13',JAN.-8

COFFFTCrXNT3 A•OUtT TuII WIND tOX,18

ALPHA CL r. D rC CM CNW CL.W LW

0,22 06055 0,1348 -"0,072 0*001 O .0,007 -0. 007

.*05 Oo.76 0,t477 "0#026 0,346 0101 00,38

4.13 0,274 0.1709 "0.0#07 0,37 0,034 0*043

61.2 Il 0,. i'49) '"9-0 47 01907 0,043 0.0497,93 00569 0 , # 231 -"0, 064 ,1 *201. 0 ,0,or 0 ,047

I3.8#7 1.120 O.6,1 "0 f.332 .0 101, 1 3. 7,.7026 9.1613,912 .1.,,196 b 46,170 -0 " ,2114 1, 893' 0,%t74 011190

1Z,96 10903 0,$ ,•01 -"0,4.19 29.1 0 "o4 06P38 0 o4F)7i

17*97 1 .,,• 3 4 0 •, 1 6 *'0 ., "u 2 2 ,16nl 0 4 42 0 697

19e97 2o770 1 4,090 -0 79 r 2 3 6P 0,701 O. n7P •

21 ,. nt' 3,240 , 3140 "--1 ,0 46 2. 17 7 04, ?,0 1 * .140

23,85 3 ,47SI. 1 # e,I,1•,") - .1,332 2 F)49 1 # , 231 . 1 32 T

25,71, 4,210 1. 97 ,, '"I,670 31 096 1, Ii1A 1,544

27,91 4,774 :, 23000 -2" A07 7,0F3 2 .5,1 1.739

29.70 5.2 t1 3 ,, 7w,62 --2. #!97 3.,464n 2,.649 1.o14 RI4

F'!

Figure B.44, Computer Tabulated Force and Moment Data for Missile II

33o Roll, No Fin, Blunt Nose

102 II.,p '..'. . ..-'-\ .• ....'••. ..,.... .. • •. . . . .. . , ,.. •,

MISSILE IITp11,2,orN1 F.N, EFl.INT NrF - II/1.1/Nr/uI,

RIJN NUMBEJMR IS 5DATA TAKEN 9t1l34 r ".,N.-76

cor'rFCUNHTS A1DOUT THP WtHD AXZS

ALPHA CL. CD r, C CM CNW CL.W(DEO)

-0, 11 -0.o043 0 ,2432 0,00" --0#079 *"04001 "06003

2.00 0.04'7 0.l,14 "'0,001 01200 01005 0,001

3.99 0.430 01'AR "'0.004 0,4EI 04004 0,00.1

5696 0*220 0#16818 "'0#007 0,7,10 01006 0.005

7.93 0.#329 06J874 0001A 1 $065 0.1".) 0.0003

9 . 03 0.442 0,2.198 -'0,027 1.330 002.4 0.021

11,48 0,593 062*•'6 -"0.034 1,602 04054 0.024

13,1 b .6911 0.2920 "'0 ,039 t ,b 01' 1 0,060 0.11,0

16 .1 0,898 0 3r,3")3 "0.10 .1, 2. 0110120 04092 00.1.9

17.91 1,032 0,s4074 "'0.173 2,339 06091 0.360

19490 .1 ,15Tv 0.4 1152 -"0,277 .7. 8, O, 0,',357 0637121.R . ,343 0, 50.4"1 2,B0781 0,t1,7 0.471

24403 .1 ,549 0, 71 R6 "0#708 3,130 0,7119 1#060

2 26, #f2 .1.•17S6 0.8607 '.1 .020,1 3350 1.40 1.#,26

27#6! .,88S5 0.9317 "-1.1066 3. 4M2 1.310 1.700

296°,7 P 0#4 1003. -"'1o407 31192 151 I. ? 1*075


11* Roll, No Fin, Blunt None

103

I

M ZSS1L.1 17133,7". NO NorILINT NOfW 1X1/33/NF/PL

_:-4,

R!IJN NUM8lfDI. 13 6-DATA TAKFN 10110$34 14.-,1AN'.-2

COEFFX(CXNTS ADl!'V THF WIND AXIS

ALPHA CL CI CC cc CNW 1110W 1,(DES)

1,09 0,042 0,1.34 --0,007 0.203 0,001 0.000

4.09 0,1f16 0,1037 -0,002 00491, 0,002 0.004

640s 0,26. 0,1725 -.0,009 06766 0#007 0,013

$47#82 0.a3UP 041930 -0.0010 1.036 00013 0.027

,a 9,94 0,510 0,2.07 -,*00•7 1.294 0.019 04030

" 11.97 0.681 0*2731 -0*003 16311 0040 "0.0000

I134113 01869 06.1.07 -0.07 1 6117 0.032 0.1M

15.84 2*094 0.4067 -0.239 1,004 04197 0.4 15

17,90 lo441 0o.176 -0,230 1,919 0,411 0.196

19.S7 3 #7'59 0 46775 -00,99 1.906 0 46 ,1 04468S21,77 l,079 0.031 4 A 'I61R 2,060 0 ,95 0.774

24,07 2o462 2s1025 "0,924 2,164 I.460 10068

25.97 2.90Ok 1.0943 -'1,301 2,110 t.0R6 1,172

I27o.43 3 20#7 1 0$1111)J -1 IS9 1 21046 2,427 1474662916 31703 1,931S "-2.02 2.137 3.001 2.043

Figure B.46. Computer Tabulated Force and Moment Data for Missile III33" Roll, No Fin, Blunt No**

104 1

MISSJLE TT YRrL.L .11,#,rNO FXNPPFNT NOSE - 11X/1.1./F/FT

RUN MIUMtER X8 8k'• IDATA TAKFIMI 081314,• ,1-,IJW-,2

COEFFICXIENTS hPOUT THR WIOND A•XIB

AL PHA CL r.T1 Cr rM CNW Cr w(DES)

0.06 -09,01 , 4123 -0,029 0,066 0 0,5' 0.019

2oO3 06071 0, 1349 "'0-032 0,197 001,5 0.019

4M01 0,1'4 0,1446 -"0#0 0,1701 0001? 0024

6.12 0 , 24'.1 0,.1600 "0,043 01 S3 0.017 0.034

7,89 0.339 0.1110 .-0603nl 1$113 0.017 O.04,1

9.117 0471 01,1913 "0,047 1,434 0.030 0.043

12.01 0.629 0,2600 -'0.062 1.7,",1 0 .030 000t3

1361111 0.74 01:103 0.0 M 11.995 0,046 00148

16.00 0 s93FI 0 36.2,P11 '-0 1 "1 2 .300 0407F) 0.240

17 1 06 110n2 0,4,2.9 -"0 2221 2 631 0.260 04. 5

19,5 1 0) R 0p, 153 -.0294 2.,970 0.330 0.416

A, 21.62 1.,445 01624, '0,39"1 3a211n 0.460 0.622

23,96 1#64f 0.7673, -0 7574 3 604 0 .,174 0,97,1

26,23 tb920n 0 9 32.7 --0.69S (393 0.0114 1.314628s14 2, 1 ,3 ,t .1 .06.10 -0,939 4.,.16 14,122 1 #7 47,I

29.69 2,270 1.9119 --1 t.144 4 . 19n I , 4 66 20090

Fiure B.47. Computer Tabulated Force and Moment Data for Missile III

,11 Roll No Fin, Pointed None

,,, ., ,..;:,

105Im

I

S. . . . . . . .,-'-., - .. -.I. . -.A++ L , +, . , +. , • • .+ j , ,• • , S , • . , • • L ' ,•

MISSILE IITPROI,.I. 33,77IN0 r.nw Pf.INT Ilflr. - .T.T.T/"'/ NF ,PT

RUN NUMPER TS 9DATA TAKEN OSIn4io0 1.-,JiN-On

COFFFX'C"NTS t6DOlT TrII WIND 6IXIS

ALPHA CL, r rIc CM ClIW CI W

-043n 006 , 0 0,3 POO .-0. "0,6 -0,023 001 0,0 45A

_ 4.07 0.'71 0. 44? "0.072 0,576 0,103 7, 0,"

6.04 00370 0,1700 --0,07, 77 ,0?•7 0.032 0.064

0490 o462 0,3804A .-0.074 1.153 040• 0.0067

9.RR 0 4 06 012199 ,-0,W71 1,446 0O1 0 1.r, 0.074

11.6A O,$i19 0o,'LO? 9 .-0.111 1.666 0o0,l4 0,094

14.09 1,097 O,,74 -.0.190 i9fl?4 0210 00.,7

15o97 .163 O41,12 -'042f19 2.0631 014t2 0413

17.94 1.,620 ,171,• "-0,413 0o 20 0 0-61 t. 0,424

19.90 1#943 0.74 1 -.0"50 2 .; N• , F3O3 06r)"9•''22611 2., 343 0,9 151. "'0 #794 11? • 0 1,. 31. 0.778

"24.30 2,779 31 a Z"o4) -I, 1:17 20738 .20 1.1 4 . ,17

2642 3 1.456 11r,203 --1 397 1 ,97 7 2,R 6 t,9

27.90 3,694 1,*703 "I 67fl 3.010 2.190 t

29.Al 4 1113 12 26PIIl)0 -.1 1036 '1104 3,01:1 1A 7 9

Figure B.48. Computer Tabulated Force and Moment Data for Mismile III

33' Roll, No Fin, Pointed Nose

106

M I SRI F I vI1, 25PF1 v I,.IANT 140Fl¶ - III2"/ ./t

:1 RIJUN NlI)nrR in 1t0DATA TtmIK7H 13t10:40 14J-,8N,-R7'

COFFICINTr ADOIT THFI 14XND 6XZEIALPHA ML. rD cC CM CNW CnW

"(DEO)

0,14 0.034 O 2%9 ' 0.04A -0. 04r 0.041 0.042

147t 0,3,.' 0 ,2•,0 "O-0042 "'0,336 003f10 0.05

4 4.01 0.810 0,2540 -04064 -*0 6•e617 0.05 4 0.0726.30 1 .033F) 0,3277 -0 0!004 "'.1,09 000,31 0.093

7*1 7t9"u .71,?3 0#4.00 -0,147 "-- 1 4`54 0.036 0.1Al

10.27 2°454 0 ,*A02, *0 . 4 5 -2.,0t 0101 0,299

12,29 3,097 0.49M -0 .4 "6,0 -0,048 0.489

P 13.C11 3.t9,4 01913,01 -0,4014 -2,914 -0,137 0,673

15O,7 4,210 31.0•4A -04,.89 -34439 -0.362 .. 012'i"• 18,04 4485I9 .1, ,63 4. 1 -0,7.7`0 '4 0. . -0,B31 14.,939

2 20.30 !t174 2.0687 -0,980 -4.127 -2.665 2.414

.4 22,03 6,172 2.4721 1,203 .-4,994 -2,41,0 3. 241

24.30 6.16A5 3.0020 -I, 495 -- 1 " 19..16 -3.616 4,313

26,01 7.466 3,1241 --.I 799 -5, 874 -4,411, 41993

•..27o97 7,S•60 4.0089 -2°.104 -. 9,9,9 -4.76P r ,.1 1 .19

* 29,1I7 81169 4.4030 .Is 470 86.1. -4- ti, 4. 539

Vigure B,49, Computer Tabulated Force and Moment Data for Missile I• . 11. Roll, Fin No. I. Blunt None.. '.., ,ntN7

• 107

"-4 . . . . ? ' r , • • • - . , . L J • • • _ • ' - -. ' ' ', . L " " ' " • ' " ' . . '

MI9,I.F X133,75pF1,8LLINT nSFl. - 7.T/Fi/JL

RUN HIJ1JMR 13 11DATA TAKEN 11137:30 14-'IAN-R2

C0FrmCUr"NTO ABOUIT T49 WdIND AXIS

ALPHA C1. CC CM CNW CIW(DEO)

-0. 3j1 Q.P1ro 0,2413 -00062 00,16 100 0.000

l•s1 00429 0,.369 "-).01.3 ".0.260 01033 0.047

4s12 0.929 0,"7'7 -0,041 -0,6800 0.032 0.067

6.14 1i421 03406 --0 075 "1,074 000,1,• 0.106

7,S7 192A6 0,4404 -0,201 -".46l 00070 0,146

10.nt 2,744 06339 -04.1~0 -2.141 00063 04,241

11,97 3,362 0.8Al6 -04204 "'.7430 0,021 0,3N3

,,,,14,11 4,*0O ' . 1,1689 -0,a23$9 -. ,, 093 '-0 01 O 1 0,437

15,67 44664 1,43,19 -06,130 -3",460, -0122 00582

111,01 ,"1 6•• It A o ,9021' "0,431q ".40037 -063,'1.1 06R75

19,67 64238 2i2978 -0s9127 -4o413 -0.544 1 163

21.f,1 7.130 20879. "'06166 -C4891 "0-483 1.603

24,.13 8,1041 3,5788 -00688 -r1,341 -1#390 2,273

24o20 81988 4C3116 --1132 -31603 .- 1,939 3.026

27.99 9,542 4.9054 -14368 -1.4690 -2.352 3.677

29#63 10,031 11 11. -.16622 -3 o374 -.20834 4,342

Fiure B.50. Computer Tabulated Force and Moment Data for Misuile I

33° Roll, Fin No. 1, Blunt None

L08

"MIIN L I IF .I). 2rF ,,I. IIIvNT NflF•F TT/II/Fi/TPL

RUN NIIN1ER T3 12"DATA TAKEN 0?ORTM ? ,1'"JANW"2

COEFFICIECNT ADMIJT TIM ITdND AXIS

ALPHA CL. CAD CC CM CNW CLW(DEG)

"-0.03 0',004 07,,13T "0,002 06,0,1 04014 0,0.04 [

1.90 011167 062140l -'0,027 -'01269 0,01i4 0,012

4.07 0,76.? 0$2333 -0#040 "'0,663 0 ,0 n 0.031

6604 1,f100 0,2907 -'0.0061 -.11067 0 067 0.041

7,93 2,632 0*374? -O,102 --1 ,142 0.097 0,104

A10 "43 2001.17 0. 93 A4 --0*0.110 s.17 7 0,11d 0,197

11.66 2,6RO. 0 6660 -0,233 -.2. 0 199 0,074 0. Pp

1 .1373 1111261 0 1 07 Il -.0633'. -3 '215 0 .01,14 00499

15sit 3,843 2. 1.'70A -0,443 -'3,6012 -*'023' o0.ro3

Ii 17.76 4 s 365 1 4066 --'04,3 "'379 "-0 'oO 141.•80 S

20602 M,004 j ,0ot9 -0,706 -5,•070 .1 o:I709

2s,77 1,400 .,1473 -"0,130 "41.0 -1 0 --1 ,,•7• ,16 8

23s93 A 0 0r 2,5~712 -0,970 "~957 -. 5 1

27,69 A. 757 A 3,3604 -1,30A -470 -7 90." 469 3 6,149

29,o I 7, t30 ,3,n0%7 -'o1, 4. "'1 -. 9"!, --3, 11, R 3s 1.47

Figure B.51. Computer Tabulated Force and Momernt Data for Miusile II

11 Roll, Fin No. i, Blunt Nose

109

MISSX I. F T 1 '7 5P IYF.1.UT NOSFT 7,7 I /r i.P I

RUN NIIM•.R V1 13DATA TAKEN 09:42:7: Ir5.-IAN--SP

COF.FFICN.HTr AIOUT TH WINJID AXISALPHA C L rC 1` CC C1,r r. Itw(DFO)

'-033 0,050 0,2230 -0.070 0111 0 ,o05 r 0.016

2,07 0* 32.-1 0,3 6 -0,042 "0 2.10 0.f0:,1 0.061

4o01 0.894 06,71.62 - 0 4 "o --0 .79 0*000 0.077

6.11 & ,37.: , 3260 -.0,0110 "4.094 0.12A 0,121

8.10 10906 0.4377 -*0,*127 .1.618 0d'9 0.1a69

11,70 3.030 0.70,46 0 -"?!I "P,746 0,1,99 0.s 7

1360 3 1764 140414 --0 o31,R -.3,431 0.108 Oo,102 A

15.609 44981 1 71, ") -"014.$9 7,4 98111 0.40717 04-715

i.9g8o 56705 2.104 -"0, 719 -1j, 027 "-0.471 1.4A9

21%'.3 6.715 2.70,19 -. 0,941, -10.6,96 -.01999 n..98

2 4 , I J 7 ,4 8 9 3 s77 1 7 --1 4 1 6 0 - 0, 2 0 1, "'J ,66 9 2 #9 7 ,1

26,06 8, 2V1 3,9154 "1 41). -6 63"' .411 3, M!.9

28,22 8#827 4, r5•93 -A, 737 6 . 0,73 "-3.0f16 429 IR 9,0064 4, 9690 1,7919 '6ol34l "-.3,6 4,R38

Figure B,52. Computer Tabulated Force and Moment Data for Missile II33' Roll, Fin No. I, Blunt Nose

110

S~~~~~~~~~~~.................................." , ' +,r ", + " "" *,.

MISSILE III AJ 927prF.1.PIJJNT NOSE Tx/ii.2s/r1/PL

R101 NUM1MWR T. 14DATA TAKEN 1n119t27 t5,JAN'.2

COFMPCIENT3 AROIJT THE 14IND AXIS

ALPHA r1 r, CC CM (NW r. I w

(DEG)

0,27 0,040 0,21i0 -.0,007 -0,066 04004 0.004

1.74 0,2117 04116a -.01013 -,0b1.2 01009 00014

4#12 0,713 0s,440 -*0#034 -00743 0,042 060414

6.01 1.O037 0,2071 ".06037 -111"' 0 03A 0,077

8,01 3,9? 63 063 2 -0,0AA "160-7 4 091 0 AJI,9 s 12 1973d4 V4, 4831. -- I1 ,231. 0 171 0, .

±•18o27 4 lOll 1 .1603 "-0,31(s -- 4,*9 11 0 , 24C 04615

2* 409

21,74 4o976 199446 ",0,493 -. 6419 ".01094 t,209

23,2 5 15 2 36,P -- 554

-6.R76 -0,E 30 A. 502

• ~.:

26#21 r), 4 2,7717 ,0,66%Wn .7,109 0,214 0,865

27,69 6,076 3,0394 ".06695 -7,'97 0,447 0,073

29.56 6,380 3,4370 "-0,791 "7.7"4 0,63 0.716


11° Roll, Fin No. 1, Blunt Nose,

"t 4.,.

,-4 HMISS1.E I1Ip33,75pFrPI .UJNT Nf18'F - /I/3.7n/F1/PL

A RUN NUMBF.R 15DATA TAKEN 15133549 1n-,JAN.-82

COEFICIIFNTS ABOUT THE WIND AXIS4,.q

ALPHA r. 1, rn Cc CM CNW CI.W(DRO)

"-0,23 -0,001 02173 -0.009 0,052 -0,045 -0,046

1,R7 0,371 0,2191 -0002,2. -06301 0,009 0,0t9

3,98 0,763 0,2481 -0"039 -0,713 0.013 0.034

6.13 1,209 0.3047 "-.0605 -'1.213 00063 00100

,,, 7099, 1.600 0,3893 -0,106 -10706 0.104 0,177

9.72 26103 0,5042 -.001.10 -20332 0.207 0,237

11,99 2,720 0,7009 -0,237 -.3,196 04329 0,433

13,06 0,916 .0,32.0 -,3,1995 0.3," O.&60

15,6 i I 1 )790 --0,419 -4,734 0,477 0# 0337"19tJ,07 4*476 ,,' tl," 17 "-0,497 "',N 140l7 0,43l 0,935

S19,79 5*01? j 1,81051 .-0,660i "-60050 0,301 1 # 2.911

22.•10 1,721 2,3033 --0,794 -6 ,792 0,102 t4790

4 24, Oro A.239 2,7302 -0,99n "7#174 0.073 2, 412

26,14 6,711 31229.3 "',1644 -7,409 002.4 1 *2 71

itq

.. 28s," 7 1 7,13A 367910 " 16,327 ".7,#67 "0,71t4 2 1 006&


33' Roll, Fin No. 1, Blunt lose

112

'4 4 * ' . .. .. <,.*.

HISRSLE 1VvJu.2'SFvr8I.,IINT NOSF. TV/11/FI/AL

!p

RUN NUNSI•.R 1, 16DATA TAKEN 11!0529 iI.JAN..2

COVEFFMXIENT3 ADOIT THE WtND AXIS

ALPHA M. C cc CM CN, C.,w(DIG)

-0#04 0.01S 0,961 -,0.000 ,-0.037 -00006 -0.006

II IM 0#29) 0*9*o"0 -0 * # -0 01001 . -0.000

4,23 0063N 02096 -0,017 "04719 01032 04.19

6,0W 0,9'17 00"030 -"0,036 --1. 127 06051, 0,056

7,99 J4232 0 34 002 -04049 .,1661,1 0.092 0,091

9 0fits 106110 0.412R -0.0673 -2.A41 0 o146 0,113

11.43 'o.094 0,9305 ".0011.1 "21743 0,229 0,142

0-1362 2,490 0 06rl 0 -?." , ,149 -*1 3111 0. 1U , 0,224

129 , 21 9 T94 0,9003 -0,0 1 T 4,,296 O.420, 0,249

17. ? 30363 1.09,11 -0,22! "'4,9611 0,321 0.211

19471 379J, 1.3336 -0,23n -"540,00 0.)1.4 0.194

21oS7 4.# 274 1*64122 -0,274 -.6,431 0.1,77 0.237 r

24.09 4.70 0 2',O2 *.0,,34 -.7.23'4 046311 0 P44

24•19 ,1,037 2,3051 "0,233 --7, 5t? , 1,003 "10,28 .

'427,85 156002 2.o5MS993 -0.273 -74 403 2,36n -Is445

* 29.72 5)290 2,1840 -0,304 .,7,s61 I.6,5 -,,4M7r

Figure B.55. Computer Tabulated Force and Moment Data for Misuile IV

111 Roll. Fin No. 1, Blunt Nose

YR

113

-. . . . . . . . . . . . . . . .-1""• "i '" • " " " " " • """ """"" - " ' "i• -••1' *•' ' - • *1 "" i' " :i:' '-' ... " :...... :"i: ••

MIS!ILF~ TVY"777'FivF,1 rPLNT WISF -T TV 77 FiI PL

R N t 1 rrR T. I•

DATA TAKE K 1I 7:41. !f"JAI•"R2

CncrF1CXFNTn APO)IT THE W1Hn A,'<18ALPHA cl. rli Cr CM rNW rI W(DIG)

0.22 0.079 0.4060 -0. Or1 "00.0 0001 ( 010P3

1 o79 0 34CI 0.177M -"-0.0 07 -.:"0,003 "'.0 0014 433 0.063 0.21T7 -"0.021 - 0,714 0,022 0.016

5,93 1,91 ), 7 "*0.044 ",,099 0.05 0.040

7*73 10261 00114 -0,067 "O,90 .07 010011

134,91 2 174 A 0.,749 P1 -02,11. -3 ý 1 0,136 1, 04313

1509 .094 0.9440 -0.190 -4.690, 04,12 00391

17409 3 0A"s 111892 .-'O33A .1. 0 0.1138 0. 0 1

19,92 4. 93 9 ,4938 "'0,394 -A31a O,0R4 0.470

21,S88 4 6,17 11230 -0447A "7. t9 It 1 0,464

25,o37 7o.177 1 4 r),1 -0, ',7 7n72 -7.710 "1,6

27,67 5 40: 2,7339 "'0,777 - 5 3,332 -141

Figure B.56. Computer Tabulated Force and Moment Data for Missile IV33' Roll, Fin No. 1, Blunt Nose

114

&

MIS .II., IIIP,.IT,2, • rF1,POINT NnS, 0 - . ,! 1 .1 S, /F../F T

RUN N NIJR.R T.S t S.DATA TAKNFII '1 0 ',27. .11 -,JIA -1R2

COFFFXCINT'S AROUIT THF wyND A:xis

ALPHA rt.. rD CC C M , fW CL.W.. (DEG)

0.13 0.0•3 0.2 19. -.. O t -006,7, 0,00, 0,004

I,#7%1 0,.320 ,2J.fl "0,021 "'0,,.3 01007 01016

3,9? 0.704 0 *",3S0 -'0.040 ."0, 697 0.0O7 0.048

549t I. :I.ti 0, IM ,1 .,0 01.7r) -. 1 'I. , 0 •, 0, 0,10 o,08

7,97 1 I Mr114 0.3470 .'0.076 --.1 61.T 0.0912 S I

11,77 '. Fj7 0.6409 "0 101,3 2 * 09 01.177 0.277

I .13o98 :1 t1 0 ,l221 ,0-.01I30 -3, 433 0 0 12 0 464

1•.70 3, ,,'6•,9 1,049,1 "'0.2,114 3,974 0I0¶',

1.8,0 43.t 1 , 1 46 1. ."0,30ý 4 65,1 0.*0 . 0 '.103

19,O1F 4,609 1 A ,41. "0, 4117• r)217, 0 O, "P 0 4 T O,?

21,79/ ,i .1, 1,4 1.9027 -0.524 "'5 , S 7 0 0,0 2 t 'a'7 8

23.7%A FP •,t A A 2,144A "'0.!,00 6 t,3114 0, .1 .1r) 1 .0133

26, 1• ,i ) 96 1 t, 12 0 "0 6 1,1, 5 6'/ 7 , 37 0 . SO?7 0 *774

S29,,1 6,107 3s4964 "0,71.3•776 .. 00' 0,776 '9


i10 Roll, Fin No, 1, Pointed Nose

i-• 115

'".'..... .. . • "" ,.. .. ....... .' " t e." . *. " " • '.e• • .¼ '.r . -. ,-' . ; '_ ,

M I SSL.F .17 Y3,-X7,rF..IFPPOTNT NOSeE "1 J/33*.7/F'/PT

RON NIOIMSR 13 19"DATA TAKEN 11i30$38 •'-.JAN--082

COEFFICIENTS ABIOUT TIME WtND AXIS

"ALPHA CL. Crl 1,C CM CNW CLU(DEG)-0.37 -0.007 0.*274 "-04033 0408r, ,-0,049 "0.052

1.92 0.434 0,2340 '.0,53 -0.207 0,013 0.031

4401 0,798 0,A627 -'0,054 -0.s"4 0.024 0#060

6,0I 1,124 0,3096 -'0,077 -.1,129 0,071 0#128

74,71 1,600 0*3774 -".0107 -10.1604 0432r1 00•,.91

10.2.A 2.*24 0.5441 '"0,171 -'2o407 0.236 0,297

11.66r 2.722 0,6707 -'0.279 -. 2%. 1V6 0.261 0.421

13.77 3o329 0,9037 -0,347 -.3, 1 01 0.203 0 .4 A4

"15 I ,72 , 9• , .) 1,706 -0 #4!50 --4#274 0,290 06V16 ,

" 17#67 4.524 1.41197 -'0,57r1 "'4196 0.16M2 t.224

20.00 5.213 3,9 11i2 -'0#723 '-5. 56 O,074 1.59 7

;, 21.74 5+745 2,2757 -0,071 6 ,1e056 -'0.022 26013

S24,08 A*4F)O 2,8363 -'1.100 ' -,,502 0.000 2o450

25.9,98 7.*tl 3. 3:.S -'I 13t- 9 -'6-6, 07R --0 ,#570 3.243

20,03 71,519 3,87r,7 -1. +726 -6. 761 '-0,677 3.*r74

29,5t. ',797 4 2, t63 t".929 -'6.52 , 7 -"0.410 3,498

Figure B.58. Computer Tabulated Force and Moment Data for Missile III"330 Roll, Fin No. 1, Pointed Nose

116-. . .-.. -.. . . . . . . .

MISSIW.F II ,2iFS.14 NOflF 2jF/

* RU01 NWIi1r ! 20

DATA TAKFN 11"OS*'1 1 i-*JAN-SP

ALPHA v I rD rC rr* CNW CLW,(DFi)

0.26 0003r) 0$2,311 -.0001 --01077 01006 0.006

2.09 0,410 0 a 29R -000119 -*0,30 1 101i± 0020

3.99 0,I00 0 6 '169T *0 #03!7 -1477 01011 101

6s14 1 260 f), 17,1%2 "0 s0 46 -1 6 9 " 00 ýf 00067

7,98 J4760 0,41TO --04. 00l' 7 "26 0 0.079 0,137

9.73 2,2311 0,:1336 --0 ,115 -- *.013 0 1± US 0019

11 7 2 2 o770 0.702 -0,170 --3.7 12 0 $3 A 0

1375 302SN 0.cS974 --0.204 -- 4 406 0 6 1. 0,390

17,S?' 4 .24 8 1 3921 --0,0 W -1 M1 0 ,70S 0,67 1

19,73 4.667 1 o 6o 67 ,0*497 "6.0 7 0,nO79 47

21o s tA2 1.904 -'0 15n? .. % 1 69 01730 0,737

23,77 5*0 2 ,3676 --0.10 --7,127 .1.14ri -04.031.

- .%

217 r 961$ 2.,70 01 -0 11.0 -7) 303 1,441 -0.782

27.92 6,202 3,0992 o0,604 --7 4971 11800 -j03 'Il

2 9.6 6.406 3o,4447 -0 679 -0 R 2.061 -t .340

Figure B.59. Computer Tabulated Force and Moment Dlata for Missile Ill

110 Roll, Fin No. 2, Blunt Nos

117

.,

...........................,.I,. T,...........

MISSLP I FT T 133,71:, YFir F11. J14T NmW -

RON NIIH•R T91 21DATA TAKFN 16:1,6118 .1 , .-JIA 1.- 9:

cOrII NTl AROOJT THr WtOTIP AXIS

ALPHA r1 r. r C rM CNW rI. W(DEO)

0,2A 0,0 , 0, 237A -0,073 -. 04026 0.018 0.019

1,7r 0,448 0.2450 -0.031 ...0.476 0.007 0,021

4 , 4,0" 0,R2 0,17r4 -0,037 -. 03A 0o0•.• 0.041

.I 6.01 1,293 0 AS -0.0161 .-1.1639 0,0,1. 0.092

11,7A 2,910 0,7"31 -0,222 -1.9fn2.4 34 00

130S ,4110 0 912mw 0..1,95 -.4,71.0 0 461" 0.481

179 1"8 1, Z1277 --0 .459 -- 6 217 0 1 ?4 0.432

206 F1 o279 J#9379 -0+601 -6,98" .1695 0.416

22*23 5,93.6 2.,740 -0,806 -7,76? ,.161 0.903

26.28 6.961 3,3417 -1,221 -8,60•3 .1,8" 0,919

27.99 7,287 N,7n0 "1.29'1 -8.7,R 2.121 06"7

29,47 7.512 1,ORI -t,,397 -8.,','0 2,120 0.312

Figure No. B.60. Computer Tabulated Force and Moment Data for Missile III

33° Roll, Fin No. 2, Blunt Nose

118

M18S~TLF~ 171 P tl :10F~vT T- Ti .r2P

RUIN NUMTJNrR X 1 22DATA TAKEN Oilt I1 4; ,1 .- ,I-61',.8

CuF.ICiI NTS (WDflIUT THI, WNIHD AXIS

ALPHA Ci. Cn rC CM CNW CL, W

bi.

0* 17 0631.1. 0$21,96 "0 0!,0 "0 0,! 040.1..1. 0 . 0 2 L"

1,97 01474 022111 "0,0,% "'047t7 0,01.1, 0,01 1

42O 40 0 951 0.,P727 -0 04 P -.1,047 01011 0.1"

6007 1.347 0.3t17 0"0.014 -"t.61.AV 0.030 0 ".

11,97 2094111 0-7773 -0#384 -3,717) 04129 09

13,193 3 s12A 0.9333 '"0,24,, --4 .371 0t141. 0.396

16.04 ,"3.914 1 .1804 -0.34I4 "- ,02% 0, 9e, 0 117

17,90 4,345 1 4206 -'0.391 --5 1 4I', 0.,121 0 1 656

19,70 4.76:1 1. AS7 -0.,507 -.6.0511 0,79T 0,767

21,06 11 6 3 • 042R ..0 , . 91 , 1 ,6 ,571, , 010 0.474

2A 2 F.•.• ,1030 21. 3 62 ""0 364 -.7,126 4 1. 9411 '"1.436

,6 :,43 s12 1 -0 325 -7,3(13 i170 -. .79Sb'

29 66 6, 4/0 3,4496 .,0,409 -7,O0 2, 1.07 -2.061

%'1 A.


11" Roll Fin No. 2, Pointed Nose

,d ol 'lot.

COp•! aLVQi di.l' ,o ivjl(. doofl iiC .""exmit. jt• yl' !•.i:Lblo 1opzOdUctlo.

119• -. ll.. . . . .

'* , 5:A: . ..: .;; " *. *.. . , . . . .. , ,*. . . ., . . . . . . . . . . L . . .. . .: . . . . . . ,

MISSIL.E TT~v1.?7vF~rPT -TX17/7/F2'PT

RUN NIPER XS 23DATA TAIF.N 0OM9?I,6 I -IN*-82

COEFFIICIENTS rIMlIT THF W14IW AXIS

ALPHA r. I r.P 0 C0 M CIr.W CL W(DRO)

0.20 0,02. 0,4217e '-06002 -0,077 -.0,021 ".0.022

1.97 0.o72 0,2330 ".010,12 *0 .111 "-,- A S "0,009

': 4.09 0.613 0 .267 -06009 -1.,09f 0 000.11

6.627 1#01R 0#340 -00039 -4 7A7 001I1 0,073

9624 1.830 0.440R " 0.09T4 -" 0'30 0d21 , . 48

'P 9,94 2#346 0,1,640 -0 ,117 -1 0 V.130 0,107 0"230

11,94 24901 0.7460 0 -3,979 0,326 0,.,367

14.04 3640.4 0,94•04 -'0,309 "4.. ,91 6.4.9 0.499

13673 34997 362010 -.0.398 -115332 0 (6:1 00 ')IS17•7•, 4'1.3 1,M003 -,,00 -1,- ,,., 0,907 0,,129

19,83I IS. 4 1!"4 1,*8716 -0.617 6*'.1414 1,0%,5 O,4621

.,* 21,91. 56809 2,3177 -0,7977 7 2. 6 7 2)00 0.R61240 A 4 , S ÷11. M

26.30 64996 3,3491, -'1 ,261 "1,S, ,1'.5 2096 0.93•

28.03 7 0 le,7 7, 'A11 --1o,4915 97F) 2 ,7 ri 0171.)3

29.70 7,7, A2 442429 --1 , .7 -7.944 ,613..U1 0.204:.4

Figure 3.62. Computer Tabulated Force and Moment Data for Missile III


120

. ..

N!BSSI.F TTYvl1.2bFPF4r PLU.IJT NOflF ~ T 7i/11.r/F3/FIL

*RUN NIJMPF TS 21

CnFFrx.TNT. AD0OJT ThI'.- W00I eV(ZF3

ALPHA N. rCr.C CM rNW CI w(DEG)

1 39 0433T 0 ,2460 -- 0 0,5 -"'260 0.032 0.033

3 OPP 0,737 0O,273r, -"0 0 2' "0 6,.$ 0 .0 V" 04049

60.116.0 t bI N41 0.3,02 -0,040 -0, 965i 01,10 1 31r

7.77 J#611 004140 ".0.069 -1,427 09109 0,104

14 o 1 .N 11,1 l0433 ..06242 --3,710l 0 2 n2 00411

17.40 4,614 1 5"590 -,7 --4,934 06~7710i

19668 9S3441 1.82 st X -- ,444 - )'50 01 1 019

a,21.99 F1 17 1 37 41 -- ,M4 -4.6 019S 1 383

2A.19 6,920 333. 03 *0o S2 7 -7,663 -.0,609 1,3~23

927.89 7 "07 37.1499 -0.9n4 *'1.0 .1 A -0.R91 3.


1l0 Roll, Fin No. 3, Blunt Nose

121

MISSILE TT1#73,75vFHR!.tJNT NOsr -i•vivr3/p

RUON N0U1R IS 25DATA TAKFN OR? 5? 28 I11 I6N-R2

CO0FFFICINT3 6nlhT THE W•T' 6XZ8

ALPHA r1,, r• rC c r CNW r•tW(DFG)

0.11 0.042 O*•236 040A -O.0l 0.00 0.010

2,o V 0#401 0,243? '0100"! '0,29r) 060R 0*023

4418R 0*?g 0,2777 ".0,039 -0 A2. 2 0,047 0 . OS

5,97 1,206 0,3346 -0 041 -. t001 0.077 0,082

7.91 IM-3 0 , 32. --0,107 --1 .!IRO O,16IR 0.169

9.82 2.341 0,3907 -0.177 -2.330 0,23. 0..93

11.92 1,076 0,6807 -0.267 -31,l9 0136A 0.464

14,02 3,747 %,O731 -0o360 "'4b0i0 0,439 0,630

15,94 4,404 4 U91 -0.460 "04,81 S. 10 0.776

17o,7 4,972 %,744 -0,9.64 1 o.l7 0,"76 0,970

19R N971 - 29JJ07 0,69'1 -6,341i 0.61.9 1.207

2t.78 Ss431 1,6019 -0 .R33 --7,086 00.193 1.*76&4

23,86 7,07A 3 e ~3 4 "R-0.9015 -7. r570 -0 ,07w,; 1.862

I 25.77 7,A73 3,6668 .-1,)40 -.M. 070 .041,") n,00

27o96 S#202 4.7707 --A.1I63 --R,400 --0.,79 3 :611

29,70 9,M7. 4,7700 -'1.,%64 -'R,)0 -.--1 750 3.069



122

: • . , , . . . . . . ..

MISS9I.F 1X1P1.'hrF3rPO1NT NOSE -1X1IFIPT

RUN NIIMAFR 13 26DATA TAKFN 0910911. AN8-JAN--S2

A LPHA CL noC ccrM r~NW C

21M6 02432 0 #.. 3 0 ~0 ,190 -.0270A 0 40 1, 05

4414.01 * 3.Z41.78 0027 "-0 4 63 -0s.1413 0.17 040070

15.7 4093 1*8 0,3281 -0.305 -40 69t 06?2 0,0l94

19o00 2. o24 71 0. 1d7R -06101 -.'1971 0,01 0.891

24011 34139 1000~ -01263 -31419 Os 10,43

24.09 6*390 2o84908 .041,63 -6 ) 1P4 04001 1,07P'

245 s79 6,792 3.2272 -0 361 -.7 o019 011. 01709

27&96 7*221 3.#730,r --0,802 --7.474 0 #t107 48

''29o48 7o329 is123 -.0,? 9 .1 717i 0091. :1 71


Ill Roll, Fin No. 3, Pointed Nose

123

MISRIIF TYI,33,75PF3PYN14T NOqC - TITI331F3/PT

RIJN NUIIMER IS 27DATA TAIKFN 0M471nl 1 -JAN-82

COEFFFICU.NT APOUT THF WIND AXIS

ALPHA C.L CD Ic CM rNW CLW(DEC)

0.29 0.032 062403 0400:1 '04091 0.005 0.006

1,99A 00377 0,11309 -'0,018 "-0,194 Ot,0 5 0.017

4*17 007P90 0,2447 --0 ,02r; w0 0A 21F) (0.03 0.041

6,08 11,1.• 0,3220 "-0,040 ".11006 0,070 0,082

7,86 j,69 0 , 4 "6 "-0#094 *'1 *,44 041116 00159

9,07 3A04 1),014 "'0,019 "'.301 0.?72 0.2881

11.92 3 0"59 0.7949 -0,o2J .3 "005 0.,40 0.446

14,0A 3,744 1,06'47 -0o3,1~ -.3.6 0ae3 00,187 0.#625

162.1 4,473 1 ,400 -0.409 -461` 0431k7 06173

19,20 *0 0 1,7933 ---006,10 -1" ' 4 0,371 •.1069

19.14 9.740 2.320R "0,742 ".'*933 0,2' 1,532

24*011 7#174 Z # P0 4 6 -3 001r) -*7# 37-.0 0.381 2, 5

2".7 7,735 ,3 .83 "- ,190 *7.374 -"0.686 2.801

27,715 Ft 071 4,2 7 21 -19.17 "7t04 "-14 4P7 3 473

29.70 k 79 1 4 .13 SY -,1,419 .,7,661 t.5 9 3 "318



124

I

Appendix C

"QUANTITATIVI FLOWFIELD MEASUREMENTS p

Quantitative flowfield measurements were taken on the leeward

side of both fineness ratio missiles (missiles of fineness ratio

8 and 16) using a 7-hole pressure probe described in section 1I-

4. Tests were conducted in the subsonic wind tunnel at a frees-

tream velocity of 100 fps. All tests were conducted of missiles

without fins and with the blunt nose.

r-

The flowfild pressure measurements were taken in measurement

planes perpendicular to the axis of the tunnel on the leeward

side of the missile an shown in Figure C.01. Each measurement

plane was approximately 4.5 inches wide by 4.5 inches in height.

Pressure probe measurements were taken every 0.25 inches in a

grid pattern within the mapping plane. Approximately 400 data

measurements were taken within each mapping plane.

Most of the pressure measurements were taken in the aft plane

with respect to the missile as shown in Figure C.01. The aft

plane was approximately 0.1 inches aft of the missile and.3.extended approximately 0.4 inches below the upper surface of the

missile, which is shown in Figure C.02. However, several pres-

sure measurements were also taken in mapping planes along the

length of the missile body. These mapping planes included areas

-1 •

along the sides of the missile approximately 0.1 inches from the

missile surface outward as shown in Figure C.02.

Table C-1 summarizes the flowfield tests conducted on the 4 dif-

ferent cross-section shaped missiles of fineness ratio equal to

8. The table illustrates the various missile orientations tested

and the locations of the flowfield mapping planes in which pres-

sure data was recorded. Data was taken in the aft mapping plane

for missiles at 15, 20, and 25 degrees pitch and 0, 11, 22p, 33,

and 45 degrees roll. Data was taken in the 2/3 aft plane

(approximately 8 inches behind the nose-body junction) for mis-

siles at 25 degrees pitch and 0, 11, 22, 33 and 45 degrees roll.

in addition, pressures were measured in planes O, 2, 4, 6, 8, 10,

and 12 inches aft of the nose-body junction for the 201 corner

radius missile at 25 degrees pitch and 22 degrees roll.

Table C-2 summarizes the flowfield tests conducted on the 5 dif-

ferent aross-section shaped missiles of fineness ratio equal to

16. Pressure data was measured in the aft mapping plane for mis-

miles at 30 degrees pitch and 0 and 22 degrees roll. In addi-

tion, data was taken in the aft plane for the 201 corner radius

missile at 30 degrees pitch and 11, 33, and 45 degrees roll.

Once the raw pressure data was obtained at each measurement point

in the plane, the data was then reduced to two components of

1.26

. ... . . . . 4 . .' .* . * * * . . .

velocity (v and w) in the crosfelow. The velocity crosaflow

measurements were plotted as a series of vectors originating at

the respective points in the measurement grid, the length of each

velocity vector being proportional to the magnitude of the

crosaflow velocity at that point. These plots were useful in

visualising vortices and their approximate locations relative to

the missile. Velocity orossflow plots are shown in Figures C-1

through C-16 for the various missile configurations and orienta-

tions tested.

& nondimensional coefficient of total pressure# CTotal, was also

calculated at each grid point and was the primary parameter used

to analyse the flowfields. C is the difference between the

40 local total pressure (POLocal) at the measurement point and the

overall tunnel total pressure (PoTunnel)nondimensionalised by the

tunnel dynamic pressure (PoTunnl1 PTunnel ),'where P'Tunnal is the

tunnel static pressuresP -P, Local °Tunnel

Total P - P"Tunnel Tunnel

CTotal is negatively related to vortex strength, since a stronger

vortex causes more viscous losses, resulting in a lower C Total

Because a vortex is strongest at its center, Creta1 will be most

negative near the vortex center. Thus, by comparing CTota1 meas-

urements for various missile configurations, one can determine

127. , 4

- . !

which missile configurations have stronger vortices and the posi-

tions of these vortices relative to the missile body. A computer. --

9 program was used to plot constant C contours in each mean-Totalurement plane. Figures C-I through C-16 show these CTotal con-tours and the values of C Total at the center of vortices in the

measurement planes for the various missile configurations and

orientations tested.

By comparing the orostflow velocity vectors and total pressure

"contours in Figures C-I rough C-1.6 for the various missile confi-

gurationq and orientations tested, trends can be observed on how

various parameters affect the flowfield. The data essentially

"illustrates how pitch angle, roll angle, body corner radius$ nose

shape, and fineness ratio affect the flowfield. in addition, the

data (Figures 9 and 10) also illustrates how the flow changes

along the axial length of the missile body. For a detailed

analysis on how each of these parameters affect the flowfield,

. refer to references 9 and 10.

"One final observatiotn should be pointed out when comparing the

flowfield data in Figures C-I through C-16. Figures C-1 through

C-8 and C-14 through C-16 are plotted looking upstream (view

looking at aft end of missile). Figures C-9 through C-13 are

plotted looking downstream (view looking at front of missile).

"" Therefore, to compare, for example, Figures C-8 and C-13 one must

take the mirror image of Figure C-8 and compare that to Figure C-13.

128

FRONT PLANE

NOSEBODY JUNOTIONM17 NIIN L14

:ii~~SI A" PL I4ANEI A"I1 PLANE

o, ~MODEL,

F:igure C,01 Flowfield Measurement Planes

o129

ft.9

4.68r ' T

A"T DATA PLANE 4.6'

(0.1 APT OF MURLE)

IIMOSLE AT Or NOLL 2S* PITCH

IlbI4.6a' -•

DATA PLANE ALONGkMUMLE LENGTH

(INCLUDES ARIA ALONG

sonl OF M"LES)

MIGEAT 440 ROLL 240 PITCH 3APPROXATLY 0.1'.......AT..RLL..6PT

Figure C.02 Data Measurement Planes Aft of Missile andalong Missile. View is Looking Upstream (atAft End of Missile)

113130

• ...~ w • ., • , ,, ..q • • .* , .,• ., . , * , . .. ., , . . .. ., , ' , .. " " ' ., . , , - - , ", " .• .-• " .' ' .' - ."' .. ., ' ' i•

N M 4 rI rI r-

~44

II~ J iAi I1 44 440U 00'U 00 U

0 0

0 I4!144

1. 04 04 1- '1- H m

131.

p

�,-.� - -I I I

Q C..� �

-

iii4

49%4 4

.9-

H

*4

N�I

* U- o cc44

9 -�

�b4 �

A

e.g gGA

4944

p4.

A b�

*

S* 0

-.

A

*

.9'

a

.9

0 .

H".4

� � � 44

�U

'.4

I� 11111

.4

8 ,-�c..i fW�4U�

I4 AA A

MN

-.

132

944*'.9�44*44�4.44944 *... � '-9 .9 9 4..'.,. 9

44 �

4 . 4 4 . . 9 . . ___ -�

v'�'.4 44 �4.4.9.9b�,9*4444I944444.9*

. . . . . . . . .

•o - *, I I. . % %

... ..,,.4,,4 ,4.4... .

4 ..... . , 4 4 4v4 't 4.. .... 44 4'"* 4N4

' -a, m s' * ', ,o -T asn•,

1A-1, MIUSILE 1, 11 ROLL, 15 ACA, IA-4. MISILE I, 33 ROLL, 15 AOA.

., 5;4 5: 4, , , 4 " " 4" ,

'" ,% j~ ' -'--4 " 4 gj 44.. ' '. .. . . .. .. .

A' 424,ll I ) 1 1 ROLL, 15 AOA.), IA-5, 5.IL[ 11, 33 ROLL, 15 AOA,

.4 ' .

.4 4'o

ItI

IA-•, MIS8ILI 1i1 11 NOLL, 15 404. 145. H ILE 111 33 ROLL, 15 A0A,4. .4 . .. .4 . . . . . . ... ..

44,54 4,4, 4444 , ,tl. 4• .

.. ,, ,,, > / .%+ I

-, .. * 4 k.l 'D _ 14- 5t, •• ,

+++1A-3, MIb8II[ III) 11 ROLL0 185 *0A4 lA-i , MISSILE Ill, 33 ROLL, 18 40*, '

.,>: :-L:',•,.:,•FIGURt E C-IA. vEL~ocIT V .CTOR FLOWFIEL+rD PROFILE•S.,-,, ~AFT PLAN•E, VIEW LOOKING UPSTREAM. :

"i 3.~33 '

:.... - . --- i -I.

-0. 10 ........ to:,' .. . -. too ...... -e,.9o•' __. -0., ,00 .. . - toel.

-6.0 .. 2

13-1. MISSILE I, 11 POLL, 15 AOA. 11-4. MISSILE 1., 33 ROLL, 15 AOA.

16-2. €•1 1 ,1 O LL, .. AO .6 5.MIS LE 1 ,•1 33 P L ,,5 A

OIL.

.0,4,

1-3-. MIWIILf 11, 11 ROLL, 15 AOA. 11-6. MlISILE II, 33 ROLL, 15 AA0.

"134

- -II l. ,"

p.'3. M1bbILE III, 11 ROLL, 15 ACA. 11"1, MISSILE, III, 32 ROLL, 15 AOA, •

FIGURE C-lA. PRESSURE CONTOUR FLOWPIELD PROFILES. ...AFT PLANE, VIEW LOOKING UPSTREAM."

4 . ... , .. . . . • , . -:' . . , ' , . .

ug ~ *~ n u I I I

S

o4*0 * .', "4.4

.

'p4 OF~ 0p 5

't.4OF

" ... ' . . . . . % %. . . .

lii • ooJJi• IiD 44 , L •H~~ ~ 40 OF go J- do N * • • • • 4 t t, I

OF141 1\ ýI ý . I I IA4. - .44.1 6

.. I , 0 ROLL, 0 AOA.. .A .. MI5ILE 11, 0 ROLL, 10 A.A.No 0 0

- O 0 O 4 4 4 4 ' 4

No 4. No

O. . ., 1\ 40 No A4 ¥114 * a4 N o '0 Ro44 , O OA,

"iO

4, 444.4444, 4444414,, , 44444i44444 * 4 ,444o 44

I4 4 5 I i I i i 4 4 * IF4 d * * I

44 ,,i',"":ir•....'! ' '"

"4 I-a4¥.1l1 II10NO.1 I AA

I.A3. MISfILE 111, 0 NOLL, 20 AGA, IA-4. MISSILi IV, 0 ROLL, 10 AOA.

(1135

.A|

:44

4,1

FIGUREcu C-2A, VELOCITY VECTOR PLOWF•IELD PROFILES. I

-j AFT PLAl4E, VIEW LOOKING UPSTRELAM.

:]. 135*14e i,44* I * ''44 . * 4 . . . . .

J UL .20 AA.2-W lmi 1 ¢•0 RLL 2 AA

alla

-IUEC2B RSUE CONTOUR FLWIL PROFILE.

..... -I.2'00 - | '*150 -

.. . -0.400 ... -0.,0S

1361

•* . .qh -O • -,3

25l-1, AllbIll,. I, 31 •IU!L., 20 AOA, ziB-l, MIlILl~f II, 0 ROLL,, 20 AGA.

;, I.;

25-3 M1bWILI, H I, 0 ROLL, 20 AOA. 25-4, MAIbblLl£ IV, a ROLL, 20 ACA, 9

FIGURE C-25, PR~iESSIURE CONTOUR FLOWYTELD PRtOFILE•S.

APTPLANE. VIEW LOOKING UPSTREAM.

136

,*1-

A.0

-4-0-.0

3A -1, IlS Sl I L 11 NOLL, 30 AOA

3A -4. MI SSILKI 1. R 2 OLL, 10 A CA

...

. . . .. . . .

.

. . . . . ..

.. .A..

... . .

A •

j * A

A A CC CA ACC, I ti I..AAA

Il/ illi- - - fq I• I

1 C 1 .

.A., r.-

I e . 44 %

SlZ

-3A-2, MI6

1Li II, 11 ROLL,

t0 AOA

3A-5. MISSILE

11, It ROLL,

a0 AOA*,,.,.........

. . . . . . . . . . .

oAA

*' *

'do * ft,

A

A At * o

A A

A

•* AAA*

C Ag CA

C C C

* * It

. .A C

A C A CAi eA. A *• *

*

• ** AC C C ,. .. C C C

CA A

S'" 'f-

7,>

,.C,' ' ''i""bI I*,I

"Ali

,

IA-I3. MISILE

III, 11 ROLL, 10 AGA

IA-6. MI1SILE

II, IS ROLL,

10 ACA

"FIGUR

C-3A,

VELOCITY VECTOR OAIELD

PROFILES.'A

C% A

1

. .. . S

A

AFT P*C '

EA VIEW

L ACKING UPSTRE

CM. .

13AC

-'.4

'"4,.. -11.9 -. 31.0

191L ,1 OL 0 84 16L . 22 ROL 2 C

"too,

382 0IS~ A1 1RL,2 O 15M16L 1 2PL,1 O

38-.1 06611.9 111 11 ROLL, 20 AOA 3 u-5. g M6 I 11, 22 ROLL. 30 AOA

p I

.OI

713

3*- , /~.**IWlL I,11j , 0AA1", *I~ L , 1 OL,| O

.,,.,5, "2I5 ....... "I.I

-...o . 1-hP5... *1.150t

.,,... -ON ... -,'1

-.1

S....... .,,,,, -l i ,,.• o 9, . -O 11

33- 1 I6IL II,I1 OL, 20AO 33O6 UIIL II,22RLL 0

-lIN138-,I I, ' -_

.. .Ljk•.rl.. .•- ."r.: • • _; .-. ¸ '. _ % m , Q° - •,% • 6 , .. ,. . . - -.-. -.-•o u .• ,',--9.,, -, -o-I. ' - , -.•. - • 9b 9.•,•

Mt 71N, ' Z

4 A - 1, , M G Mit~ 1, 3 3 NO L L, , I 0 A O A , 4 A -4 , H l Mtl L E 1, 4 51 NO L L , 20 A GA .

M.. .. ii . .. . . . . .. .

"""•99 1LI i'"~ % "'•••,• ""

/ "

4 A 24 . M- , ILE 11, 33 RO LL, 3 0 AO A , 4 A- 5. , M I Sl IL, I , 45 NOLL , 20 AO A.

. .. ..A,: , ,

op ' 'o * • • I ,•"

4A -3 . M MIiLtL,,, 11I, 3 31 ROLL, go AOA, 4A -6. Md b$ lLi• 111, 4 51 ROLL, "20 AOA, .

•." '":-",'FIGURE C-4A. VELOCITY VECTOR FLOWFIELD PROFILES. ,

;,', AFT PLANE , V IEW LOOKING UPSTREAM.•

*9139

• '.9' 9•='', ., .' .,• , 9... .9 ,.9,9 . . . , , , ,, , ,.* 9 ,. . .s .. . , . , .. . . .

-fail

•,,' -O.6o•-ie.,o i;

",, someI

440

-I,,

41.I3 MISSILE I, 33 ROLL, 30 AOA, 41-4, MlISILE I, 45 ROLL, 20 AOA.

FI R .. P R C U I

'.°+,AF PLANS VN' + "IE LOO INGUPST EA . .I, "

7'I U+_4

i3,5 Ki, *, I,

S4-3,2 MI~bILI III, 33 RAOLL, 30 AOA. 43-5. MISSIL[ III, 45 ROLL, 30 AGA,*

CYTL______._________________

4S-_. M I OUII I E3 C-4OL, 30 AOAR 4OSTOU MISOSILED IIO•I, 5RL L, 20 A..

.•APT PLANE, VIEW LOOKING UPSTREAM, p.

XFLOW 5.6 XFLOW 5.6

.. . .... .... .. , I I I . ..... . . . . ..I

a.. a 0 , ,b Is

•l I I I t $tI t f i I qi I

i It I I ' I f$ I IItt t

W t .0 *IB I t o, f L I IS O -2 I I I 1 1 , * O 0RL L 2 100A U

"*. .. ,, , . , ,, z ( ,C IDD .j: , ,,,,, z

"0 JJ •• ' [11 ' '.. ~• •I ! , ' I '1" " il% I

M-,owl *l -FLOIil . 5.6,..,, 0 00.O0 *I5 5..O

*, , - .. ...... .. .... . . .0, *, ,. *.. .. .s. .. .5,

0 0 0 0 0 . , o o e o e e s htit ti i i t 0 0 0 5 0 0, . * * e e , StI I i I

I LI I I Ih 4

1s • I4 pose i lb 4%

11111 hill 1. Fi t

-3.606 3.666 -3.686 3,666j M-3. NZUIM Ills Of ROLL, IS0 AoA SA4. IIIILI IIIP, Of DOLL, ISO MAD

.PLOU . .:,,6

f~ a 64 s s sI

tol.,.,,••|% . C, Sli 1" ,,L,..%

I.,s

dl1l I 1 .1 . a a i I a Ill l t

$li -1 II II I IV, Of RL I ADA

• *~,,*,~ ,,,, ...

FIGURE C-SA. VELOCITY VECTOR FLOWFIELD PROFILES.

I I '""

AFT PLAN, VIEW LOOKING UPSTREAM.

14-.1

,, ,I-,

.4A",4

1 MISSILE__ - 1,$ 0 RA, S11

•.'+5 -5 MISSILE IV O, ROLL ...... A. lO,,,,.

,.,,,";,,'SW

*142

• .mll.1,111

*i 4,'-- J ,V'A __ •._-m;._-_;-_______

US1-i. MISSILE I, 0 ROLL., "+ AOA, bS-M, MISSILE II, 0 ROLL-, 35 A0OA

, -- .. - Cv* 4S ' . . .. .

.4J ,,

'I.•

,'| ! 4,

-+3" I.

-- i +I,, 0

FIUEC5.PESUECNORFOWIL RFLS.4 +, ,)

AFTPLNE VIW OOINGUPTRAM

.-. 4

%1.

4.•'tl *l

"Xm"6,5" s. X" O .S 6.

•,l* * * * w p o o w i4 4 4% ,, *4 44 *4 * 4pl l l4 144. I .i. . . . . * . 4 t . . . . . .. . . * . . . .* *. .

ý kW 4 ..644** * 4 *~

-.,° * * *" s *e * l.. * 4%

. " 0 ' 4 '4. *" --- ,,.."gt'-P- ----.

"" 1, I RL A. ..it OL, 2

60 44a

Ole in

.. 04 o ,,' "%'

3.0000 -366 3.666"ill I~l -- !l T, l

M', MIllSILE 1, 22 RtOLL, 25 AOA. B A-4. MIMSI II, 22 ROLL, 23 AOA.

.143

4 I I I I S S i 4 4 I 4 I 4 4 4 4 4 4 4 4 4 4 4 4

4 *4 t t 4 4I I 4 4 * * * (t * • * * 41 i l * l t i . i . l , i

. , , 1 4 5 4 4 4 * 4'• 4 4 4 4 4 4, 4

, , , I * * * j l i i l 4 4• •

* ', , 1 • I 11d• I l l S * ' ''? I' * u , I t

u C' ''• . C' * j ,.

-"3.066 3,660 "3.0OO 3,OIO

"" M , 3 . MI SI I L E i I II 2 I BO L L, 2 5 G A - . I SI•, • L E hl X I P , 2 2 I Ro L L , 2 5 A CA ,

4 Sd

'4• AFT PLANE, VIEW LOOKING UPSTREAM.

--. 4. ......... . . . .-- ".-,,- '' •------• '"" -- • ,.-..•*

.. ,. .. 00 - -1,

-1. Ie, 1, 22RO..........1.-2..........1..... ......... .- is ,

N-1S

'4144

S.... "e•i*......".,10

- . 66a, " , 0.1, .66 * -O.,5

* OS-I. M*bI•SLE I, 22 ROL .L, 25 B*OA. ** -. , MIMiSILC II, 22 ROLL, 25• AOA.

k. . . ,.--.,,,,q

"* W

.4W,

SlIa.•,•'

%/

* -* -,$., '. ,'o:

Cu ** . e.e ....... ...

". .. ... ... . . . .... . ..

So 0 0 Is 0 0 0 a 0 6 1 I. 0a0 * E *. . .

I /,..9,tiillj tj , 9, • t I I l ee

topl

lll'r ' | oh• IIs,;| t -I-- .' I'" I -•..

-3.00, 3.4O1 -Jse 3.600?A-I. WiIIt.I 3 245 SOLL, 15 AA. 7A-I. 41851LI U. 45 lOLL, 25 AOA.

. 6.0 0 6. a 0.5 6. 4

***" * I, e II 4ok

*** . ... . ........9 "2'.. . . " "' '

.9.

11 t llI

7A3 HI:Ij I 43 12 - 4 I IP, 11 ROL L, ¶A

z" '"I

t lA-.1132. \ 1,1, 45l. LL 2511 AD. At.141331 KEl 4 O ., 115 ,MA,,

FIGURE C-7A, VELOCITY VECTOR FLOWFIELD PROFILES.

AFT PLANE, VIEW LOOKING UPSTREAM.

-9 It145

*.* .. -

-"A

-*1C

* CIOAI. CI

..... ... f . -.114S... O* .---0

78-3. -6 6 54S"0, 3W=. - -- h1

' .1,1. .1,I,

-htI .hi

* |IsuO . . . -* -eON . .. ,5

-l-1. M1ISILF I, 45 fOLL, PE ASAU CO-NT OISILE II, 45 ROILL, 2 AOA

.14

&t MA "1,11

S( A

-71?-a, Ml~bILL[ III1.45 MOLL, Rb AOA, 73-4, MltMlLC 411I', 4U4 ROLL, 25D AOA, .

'SI:

FIGURE C-7B, PRESSURE CONTOUR FLOWFIELD PR•OFILES.

AFT PLANE, VIEW LOOKING UPSTREAX.

II.

~i.

I~ l

I~- i t ) U . i i

f958 e 14.A-,M~bb(Lf 1, 11 ROLL, 15 ACA, .4-I MISSILE 1, 33 POLL, 18 AoA.

4' 4'. Ij It 0 o -0

14 hi mjv %

'.1 .0.0% 4'' ee l% %

4 A-2, MI b I La I I, 11 ROLL, 20 ADA. $A-$. MISSILE I I, 33 ROLL, 15 AGA,

.I'4

'.4 4 0 1, '

10. 4 'o 4

40,0 4 0 . fog-

4,o 'o ' o, ~4, do 'l OF .0 1 l N

L~ 4 Ir wo lo 1-a ,., ~

0 o

* M'= 4 b4L4 1 11 , 11 R L , a O ,G . M S I E 1 1 3 R L , 2 I A

4147

i.!

.4 AO-,L t cO4tY k

.I.afO - .2.5

------. -0. "o1 44, 0,* - 6,i00 .- ,60 0

-5.000

1 -2. "I, 30 11 -1o -0 1

',ii .,.', I

bNI

A ELI

v /, "~flILE .,"..,, ,LL4+ 1- , II IL , ,] R ~ 3,5I A DA, Ii-4, MI 5IlIII I, 3,3 ROLL, 21 ADlA,

.4• .0,ll .I,1I

."0,61 .112

II MiSSlEll IIi1 ROLLI01I,, iMb AOA, 68l-8, MIllllSI , 133 ROLL, 35 AQA.

'4.4l..4

* , .l t. -. I.I 1 ,,,t ,

',• " 5 (. I lt I L L- I I I , 1 1 H Ull L L , il , AO A . Il - i M l Si lL E+ I I I , 4 i R, O I. L , + b + )A , A ..

FIGURE~ C-S. PRESSDUREI CONTOUR FLOWPIELD PROPILES, .--. i

APT PLANE, VI.W L.ooKING UPSTREM.,,"::':':

4,.

S _ . . . , 4 ,.. L,,..m " ' ' ' ' • m " '

BA NIB11SLEMOLL MtAMIHA lIO'APFT IA0 MISILROLL MAMiLPMA IJ,4.1$Pr

CTOTAL CTOTAL . 03

.... -Ih '00*. . -,leo.

so-- "O1I106, llkmM3OO140141 HW o F

*4.,610

*6.369 IO

-i ll

FIGURE ... P, o ,R E CM LE

0

22 ROLL, 25 AOA. 0-2-4-6 INCHES AFT OF NOSE-BODYJUNCTtON, VIEW LOOKING DOWNSTREAM. INCLUDING SIDES.

"414

r" &SM

•'I1 =

0 .

£0 MISOX IlLIPOLL. fl,ALPNA 11,90Vr £0 11155t1.,1101.1 t2,APNA 25,4.I'eP?

I * * * *

00 go 'o 0 k ', ".••I

. op. *\ .1

"]liI~lll'd~ , e : * ::;L~t I,'ll Hlll|I,111 II*t- 114 I T•"

•I *.' a++ II II * ** l I e ' '

% I. El, , g i.i.i•• . \ • t + , ' '

- , + + ; , I, , • •

* hl

I6A

6~ .0 do

*N L

T•, , ,

.55

SO NBIIIOL DLP A i i M CSIS tIO L a.L NA 1 4 k

._4.,,, i

] rI

- 2 LI25AA -246IC}E • O• -O••D ]

JUNCTIO , V *E LOKNIO.TEM,•CU[GSD8

a.,,

I0 10i .I foROL.L 8, A.LPHA Ito 10 AFT 10 H lLI.lOLL IIt ALPMr 2. IWAFT

-COA CTOTC L .2.0. .... ... gO*L . .- • . ... .

.: :.. ....... -4 ,.Po

+ ,#+'" '•+ "J0'"s+

.,.,, ;.,. ';,

4.0.

"".o 1 .o-3 . 343.

-loiNoil

O7 l.,m A

FIGURE C-10A. PRESSURE CONTOUR FLOWFIELD PROFILES, MISSILE I22 ROLL, 25 AGA. 8-10-12 INCHES AFT OF NOSE-BODY "

JUNCTION. VIEW LOOKING DOWNSTREAM, INCLUDING SIDES.

i'

-I, IA

.3. SW 3.

'v°,'

V~

"16L9||l IIlOLi. Ito ALPHAk no 1" AFT 60 N1t6iWtLe,llI Ilit AL.PHA no* Ill'il

00, e |, ,• ',

4',0

,' IX Lt''

~ 4444 h *9•t tt •{

.4* Vh~k iiG~ I*fl P

'• , HISOIL I. Al l ,AL. g AS, IS'd APTq

:. %:;.:\

"9,,,

ailO 3.3 "

ITIGURE C-lOB. VELOCITY VECTOR IFLOWYIELD PROFILES, MISSILE I22 ROLL, 2.5 kOAD 8-10-12 10LItCs4 AFT OF iOS-BODY

JUNCTION. VIEW LOOKING DOWNSTREAM. L•NCLUDINO BIDES.

ado

152

.. '

-- -1 i

*4

11161M I. OLL 0. z,0.0 "as, PA to MIUkIM I, POLL I t. , 1BUM? HO .ALP ii k%L ?OI~tNE. __,________ ,OThEt.

.4.4

I-I

NI-ILI I, MLL 23. e 6i geg, MIS ElI lo RUL 33l S.E m",U.pEE Ag.TOTAL

NISIILI I tOL 41, SLIT mus, ALP" IIcGiftO

L~Ri A. ,4

~~II

FIGURE C-IIA. PRESSURE CONTOUR FLOWIsuLD PROFILES, MISSILE I

": .':.: 0-11-22-33-43 ROLL, 2/3 AFT PLA•E±, VIEW LOOKINGDOWNSTREAM, INCLUDING SIDES, 25 ANGLE OF ATTACK.

153

do #1

n i g l~ t. h PO (k1 .O . PL sI 8? MOi. I L. PMi IIt N1 1 L I0 l O LL IN , ILN ? N O P. * L P i t I

'4 4. ,4*44

Jil,

JIL 1II' "-3... 500'

a0 J

4,' ' ,., , .- -,.3,.,.I

w1511IA. O, ALP Nil, i , ALH U ,IOLI MU. - --W [email protected] • *

4.4

',.•.•/ lI , ,.:., .,

,00, p-

I?''i I j lilIU.

"11. ' ' % • . tI •' '.'"

FIGOURE C-11B, VELOCITY VECTOR nLOWFIELD PROFI:LES, MISSILE I

0-11-22-33-45 ROLLP 2/3 AFT P, ANEj VIEW LOOKING

DOWNSTREAM, INCLUDING SIDES. 25 ANGLE OF ATTACK. "'''

N+ -

*,,4

mIIiaL! lh ROLL I. ILMT NWo RLPNA 18 NI1it1 II t ROLL li, WLIIT NO1, ALPHA 15

. , -.. CTOTAL . ,S

-0.400"...- 30

.t14

,4.1

i++m-aH S *IS '.--.,

lIIU hI 0LI III OWL ll UNY WHO ALMI il6ILIl lit RILL M1. lK Noll, 4I1P10 IICIOTL OTOllIL

0. 4

F11o1i Hi. NOLL 41j 1o 61MIO,

'42

1 711FIGURE C-12A. PRESSURE CONTOUR VLOWIIELD PROFILES, MISSILE I1

0-11-22-33-45 ROLL, 2/3 AFT PLANE, VIEW LOOKING

DOWNSTREAM, INCLUDINO SIDES. 25 ANGLE OF ATTACK.155

155 i

............~ *4' * . • o

"* i * ''' *,** *,

;100149 It, AOOLL 0. ILNT NOB, ALPHA 11 M1111LE 1t, 004L 11, 107T N0o ALPHA 11 OP141 IIB-JUL-Sl1

Ap .0 0 10

DII lilt%%.

111191SI to JIMOL 111.8o ILMO OY 1406o 5 ALH11151101 Iii RKIL 34 510? most 141,1" is

'p p

I,.It

AM 11AN 101 46PO 11

Mill

FIGURE ~q~%% C-2.PESR ONORLWI ROIEMSIE1

0-11-22-33-43% ROL,23 n LN, VE LOKN

DOWNSTREAM,~ ~~ INLDIGSDE.25AGE. FATAK

44'' '

HIMI fit ROLL'Ok 1WH 1401, ALPHA 15 NflILSe flit RDLI. lit KOT4 Ma, 4IJIWA 85

-tell 114

a'4

'

o I.

FIGURE C-13A PRESSURE CNTOUR nowILD PROFILES MISSILE II

0-1122-3-4 ROL,23 AFTse PLNE VE LOKN

2A.-

1 1-ILC II,, QLL 0, WIT 140 .iLONA 95 HIM 1.9 111, MOLL it, UN I IMP , 1 A

... ,, ,, ,,•/ . • ' ' • .' • •

it ,,,,',, " " p p piI,,,if i I II I I1111 % & & II5', II~lltll l I i l'll

46iLII 11. POLL. 2 1 .1i? HO91 , ALPHIA *18II III , ROLL 13.,, ILI.T 08I. AL•HA

--'... .'4 ."

-.. '.. * "0 ' I t

I ,.,4 -;% I% It It

1001 01"

,,•., FIGURE C-13B. VISELPPOIT VECTO *LNIOlFsDPOIES ISL

"116 0-11--33-5 OLL 2/3t AT PLANE IWNLPHA it

.vWp.

II

'I FIGURE C-13B. VELOCITY VECTOR FLOWFIELD PROFILES, MISSILE III

0-11-22-33-45 ROLL, 2/3 AFT PLANE, VIEW LOOKING

DOWNSTREAM, INCLUDING SIDES. 25 ANGLE OF ATTACK.

.15

_., . *. .',,S - ,

i:.• ,. . ., , . . . -, . . ,. ... .. .. . . . . . .. . . .. . . . .

fttSIn I h IS LL. OL IAPHA It IRit|L| . POLL S, ALPRIA 31CO, , CtOAL

.. . -6,41

-0. 3" lb

-!W r.''>

44.. t. ' ALPHA .

a,.

~~~~~~~~N61. SoIIL "LL Is ALPHA It•,P••Iqlll4 iL o•~

: 11

'Oft" 4 I| I.II - "

.• MIIIL I, l~l l* ~l.Pall

0 RAN

4'14%'

4-'I~EC1A R.8UECHORFOFED RFLS 2SL -

U• ,...1..

•",...: 0 OL, 0 AAAF ?LNE VEW OOIH •.T4A/

" 1 11 4 1 16 1 R N A 0; , O , .4 •P H , W • Al$ t I t O L 6 0 + •, A P H A q 3 4

% st

'Ill

I •s I"IS 4II9

\. l.9Id 1' .'

M . . . .P 06 O f A L " 3# H O O f N O L . . . . A L H . . . , , 0,

, " 0, !`f "t If • : , If

-.- -,

00l o -% % % 0 -

t -4

M tCULi I, PILL I, ALP A 3

1 0 :

• i I, • x l \%•' 49 ' . LS\ I 9¢''

' " + ' ". . . " '

St/ , , ,"/ /! F I /,i. i

""0l ROLL, 30 A, AF PLNE VIWLOIGPTEM

""ln i I, o9160+ -+- : .. . ,II

9 I I

I I I

, , in,,,,9,, 9t!

• 9 • ' I I I [i' - ~ o

• l J I . # I.I

'4qlIi @ .9 9¢. . . .4 9-

. . Iil i i i , 9 9 ' '

.919••

+ • + + 1 r L . . . + ' ' ,.+ ! : ? + ' , : , , . * ' . * ' . " ' s . , • . , " " r

-o'UI"I

... . -O U.W

I1~111

~L R~

I~

5... 0

Cop I

4 L"A"-

,'

.1

•,

., " I'

mnot~ ~ ~ ~ ~~ NSI to NOLL $i

h• •

isll+ OLI,•

+

.161

OIOII0,,LL*0

,*I Itl+ .*U i A

IIN ___ ____ ____ ____

t lI

I •

k l

I •'+ "++4

• k"

i +. +. l'l._k - , • •+ . , k m+

+ +I+

i

IO Rl LE

, "

"

".

.

.

.

-. 11

"1I69MI I N OL , AfI4ALPH I MIMi I is POLL it, ALPHA 21

ft.......tII" "'...........'I"we A. . _

% -

" "-- - - - - - - - 'ft " "% % 't-% t- I Ift. # ft. ft.• % a . %

• ,, ,• , % '- - . .. ,• ! " "

...... Eft- oV 0, -o 0 4o i

No w, 4 ,0 ,II II

t. OPP to - - ft

lt -. , O

41 % % _ _ _ _ _ _ _ _ .. . .' .

__________ 1 7ft-SIID U E*. *. " ft I ,,*

Z Z OR--0 -4

do so Z A AT E,*VIE LOOK * G -*"

0 - = ~~- - -.t - % p Z'

... ,

hiliSOLI N.OLL i. ALONA 36

'Io

22 ROL~o 30 AO~ AF PLANS, VIE LOKN UPSTEAM

162

S -• +. - . ++ : • . , • ,- -. } • g e • -- • 'a +% • . , • , ! . , , . • . - ,. , . • . . . . . • . -

011II1,1M At I•, 0% " I tl 141,1 3.

4I-.... - 1. lot

* I 1"•

0 -13!I :

HISL .hl Hil 1, 7 1116 A 4... .,IW•u.0;\ ". S

R 3

Nt$IU 2.SIU.t... $I,.S m;OL 24

'• IIIII.I l I•.I. I, il• 1III

.10i43 4.1

FIUR C-6.PESR 'NOaorEDPOFLS ISL

•r ' ,22'+l

0-1-2334 RL 30 41, AM

1634..

* 5'4

*! I .

' "&""[,(• t

.I ~0-11-22-33-45 ROLL, 30 AOA, AFT PLANE, VIEW LOOKING UPSTREAM. '

'S..2 • M '.. *.'. 4 *' . '". 4 4..' .'• .', '• .. % ,44'*444* ,.. 4, ,* , *.. ' ". ", o, " , , *,,* " . , '4 . , * . .'* ' . .. . - ,'.".. . ..

HIIIAItL I P 601., , ALPHA 36

""161116I 1, MOLL It, AiLPHN It

,,•~ .- -- .......... ..A .. .... .. ,,

IS %

-.%% %iN 's

Ft•.•~V ...... 'o ..

#11111,1 31 NOL It -o P 1t, 110 MI MI MOLL 340 4004 3$

Ito

, ,,

t ... ii

.. *

;, .- 5 so 4'.

S,•Al

, - . : , ,0 0- 'v

• ,1,-..-.. -dl

0-11-22-33-45 ROLL, So POLL40 NLP T 14 N ,VE LOIOUSREM " "

toFIGUREI C-6B VELCIT VECTO 11.911L PRFLS MISSILE 3~t 4 1913

164 g 4

?:!*:_--;•-:_5eS5•. S-SS iii•'-- "- •: :"-,,"-:.: : :..,--:.-. :.:.-.:.:. . -_. ,:. ..._ _.• -. _ ,. ,, .

APPENDIX D

Tuft Grid Photoqraphs of the Flowfield

Qualitative flowfield data were obtained for various missile con-

figurations and orientations using a tuft grid. These teats were

conducted by placing a grid of wool tufts in the flowfield on the

leeward aide of the missile, and then photographing the tuft pat-

terns. The tests were conducted in the subsonic wind tunnel at a

freestream velocity pof 100 fps. All tests were conducted on

missiles without fins.

,%I

-p.. Figure D.0l shows a schematic representation of the tuft grid

Pteat setup. The tuft grid was placed at 3 locations (forward,

mid, and aft) along the leeward side of the missile body, perpen-

dicular to the freestrean velocity as shown in the figure. The

forward plane was located at the nose-body junction of the mis-

sile, the mid plane 6 inches aft of the nose-body junction, and

the aft plane at the aft end of the missile. A camera was

mounted downstream of the model, and photographs were taken of

the tufts in each of the 3 locations.

For missiles of fineness ratio 8, photographs were taken of tuft

patterns in all 3 flowfield planes. The four different crose-

section bodies with the blunt none were tested at 10, 15, 20, and

,, ..•......- ...- . . •., ... .• . .,. , , . ,_,,.. .. ,-. • • . . .•,_,__

25 degrees pitch and 0, 11, 22, 33, and 45 degrees roll. In

addition, the 201 corner radius body with the pointed nose wasr

tested at 10 and 25 degree pitch and O, 22, and 45 degrees roll.

Table D-1 shows the various missile configurations and orienta-

tions tested for missiles of fineness ratio S. Figures D-1

through D-23 show the photographs of the tuft patterns for the

various missile configurations and orientations tested. Since

the camera was mounted downstream of the tufts, all photograph

views are looking upstream or at the aft end of the missile.

For missiles of fineness ratio 16, photographs were taken of tuft

patterns only in the aft plane. live different cross-section

bodies with the blunt nose were tested at 30 degree pitch and O,

11, 22, 33, and 45 degrees coll. The square body was also tested

at 10, 15, 20, and 25 degrees pitch and 22 and 45 degrees roll.

These various missile configurations and orientations tested are

shown in Table D-2p and the tuft photographs are shown in Figures-.14

D-23 through 0-30. All tuft grid photographic views are looking

166

I" s

"• ~166

• . . - . ',"" ' . ;" ''-.1"," : . 2 " '. :" . . :"; .".'. . • ' . 'i . i." -. . . -, : • -- " . ' .. , '. ' . . .- ' . '"

V°I.

I'I

I'II!

iI

II

•','

9J4

a I*! I5

• I • Y • i@ • " L• t • t a1 I B I "• t •i • • 'D "i ' i • I. k • • 1 -b ." '1 I . . , l ' . I i.I a.#, • • ,

.4..4

.4 1. . 4 H 0 4

-J

4 -'- ht'U

U 11111111

2S '� :�

!� r�'I

Ii.

I,'

0 0 B -

A A A a. � Sb- C USe .� to4.- a a a �

0 0 0 0 SIB

rn-I

AAAAAAA EJ� i�.i iihi

Ii Ii � 11411'U

S

4' - S 0t�m �hi

.4

4.

4., B,

14 E�u I*'. N I.d�

I, K K' -� ...4.', " ,� -W

'v.45 � �Nb.aNg w.e@o

�1%

-"I

4, N IIIi..... 9!.4

169

* ,.I.,,,,I-...t.. ,.,'.*.*�*.*..I ****.4.** *-*.*.,�j.' ...-.. *'�*'***.**.**.*'.*** '-,..- 41

0 4?

41^

%.

P4" -4P1N m 0N m 4 L

* 170

'12e-

ii

Ia. MISSILE il a~ Rol.L., to 0 PITCH Id. MISSILIE 1., 00 ROL.L, 25 0 PIT'CH"I•1

0

lb. MISSILE 11, 2 ROLL, 10 i PITCH ld. MISSIXI 1, 22 ROLL, 25O PiTCH

ibo * ISSILE• I, 45° R•O~l, 10 1 ii It *I Mi, HLSI, 4, RU2 I,I *. "2 P lWrt

FIGURE D-I TUFT GRID PHOTOS I N FORY'ARD PLANE

FOR MISSILE OF F INENESS RATI10O .b

171

-. - -'-r-

2a. MISSLI 1 0 ROLL, 10~ trcum 2(l. MitSM;I-IE f , 10RI.L 2' ITCHlb+ a'•~ ++++ I+• ++- ,."

2b. MISSILE 1, 22 lioLL 1o PITCH 2o * N MI A r1, 1.2 ROL, 2 5 1TCII

*1o

'2c H. S I 5' o l 6 ." ! ' 1 T ;

.+,ý 10 " II T ý J I "

F I G UR E 0 -2 UP F r GIt1) P H( [ 1 0,) N M 11) PL ANEFOR M ISS ILE OF F INI NEL,) ~Ai10 1

i." j mlPJ + I• 1•. PJ [71 ?

3a. MISSILE lo 0 0 ROLL, 200 PITCH 3b. MISSILE 1, l11 ROLL, 20 PITCHi

I3c. MISSILE I., 220 ROLL, 200 PITCH4 3d. MI SSILE 1, 33 ROLL, 200 PITCH

30-. MISS-ILE 1, 450 ROt.!, 'ŽooTC

FIGURE U-3. TUFT GRID PHOTOS IN MID PLANL

FOR MISSILE OF FINEN'ESS HRArIO 7 .5

S. I.

""--' " '*,'',,I m • l .ftI 'I '* ..-- -- -l i • vl,

41+

4a. MISSILE 1, 0 0 ROLL, 10 0 PITCH

4b. MISSILE 1, 22 0 ROLL, 10 0 PITCH

4c. MISS ILKi I 45 R01l,1 1 1 IITCH 4

~FI GURE 0-4. TUFT G I~ C, ) 1C., t~i I N AFT PLANEFOR MISSILE OF F INE NESS R v 10 7.

1/4

1'

5c MI 3 .1 .,L jI 5 M SL ' . *RL ,.5 IC

S... 14 10 b

F'

54 .SSZ:L~I• 05e ROLL, 15 PITCH 1b ",IISLE I, L ROLL,, R5L PITCH aI

FIUR Db TUF GRID PHTO IN AF LN

17

lii

S€. H:•i$~ I, 2; •IOL, .3 5d '4I-sSIL' z, 330 ROLL., iS PITCH

r• •J ,• _L

!,,iM .1 " [r [, [• '•J rJI.,

• e, MISSILE, I, 45° ROLL, 150 PITCH

FIGURE 0-b. TUFT GRI0 PHOTOS IN AFT PLANE

"-- : FOR MISSILE OF' FINENE.SS RATIrO 7,5

175 :.

6as MISSILE I, 0 0 ROLL., 20 0 PITCH 6b. MISSILE It 11 0 ROLL, 200 PITCH

6c. MISSILE 1, 33 ROLL, 20 PITCH 4020P'16d. MISSILE 1, 45ROLL, 2 IC

""

* .1

FIU6RE Di-0. TUFT GRID PHOTOS IN AFT PLANEFOR MISSILE OF FINENESS RATIO 7.5 R

176

7a. MISSILE 1, 0O ROLL, 250 PITCH 7b. MISSILE 1, 110 ROLL, 250 PITCH

7c. MISSILE I, 220 ROLL, 250 PITCH 7d. MISSILE 1~, 330 ROLL, 250 PITCH

7e. MISSILE t , 450 ROLL, 25011 'T(JI 7f, MISSILl" 1, 4'5 ii'Ol, .25 Pi'rcH,FlN CONF.

FIGURE 02-7. TUFT GRID PHOTOS IN AFT PLANE

FOR MISSILE OF FINENESS RATIO 7.5

1.77

--a--. MISS IILIZ 1 , 0 .. .. L, to... P-,T CH 8,d, M S ILE 1, 0 [ 0 .ROLL 25' 0"IC

8b MS ILE It, 2? ROLL , 10 PICH8, MISSIL:jE!r J - IT 227 ROLL 25. PITCH[.

0 0

8c. MISSILE '1, 45 ROLL, 10 PITCH 8f MISSILE 11, 00 ROLL, 250 PITCH

I,

%1-1

A, p

a,,

Sc. NISSILE ID, 450 ROLL, 100 PIT~CH 8.. MISSILE li 450 ROLL, 250 PITCH

>' ~~FIGURE L1-s. TUFT GRID PHOTOS IN FORWVARD PLANE....

FOR MISSILE OF FINENESS RATIO 7.5 .,';

o'I

S.. . .,, , .*.* ,.,,. .'.*.*.. ,. . ... . , ..... , ,.,...... .. ....... ,..... .. .. ,-.- . , •', .,.

I - .J J i.* .. . . . . ..I I IAA

gas MIS5SILE It, 0~ ROLL, 10 0 PITCH 9d, MISSILE 11, 0 0 ROLL, 250 PITCH

(4b. MISSILE I1, 22u ROLL, 10 PITCH 9.. MISSILE 1, 220 ROLL, 250 PITCI

4*I-

.4

"9 C. MISSILE 11, 45 ROLL, 10° PITCH 9d, MISSILE It, 450 ROLL, 250 PITCHu

FIGURE 0-9. TUFT GRID PHOTOS IN MID PLANL

4.'."4_N. II41d ,0. . -

'•!I qbFO MISSILE If 2 O FL FO INENES RAT IOSL 7.52 OL,2°PtCI

179

a..%

,.4. 4 . '

N Ia, NIS 8.IE IIj 0' ROL L, 100O PITCH

44i

4.

*; lob. M1SSTLL [I, '?° RO~LL 100 PITCH

'*,,.

.4."

4'4*I c Iq I ,E t . ~ , OM , 1 ° P T I

A•F GR -O U TG I H TS I F L N4*4. . . ~ ~ .• ,-; t A 0 i' b ,.1%•;F R ISIE O

.4.i

,'44 ,:,,,,•• .. ,.,:.•• .,.,,•,,,.., ... .

• ,I iI'

1,1a. MI,1,• I I I, 00 ROI.. PI'•• l'l l1. MlSS1 1, 110 ROLL, 150 PITCH

S.•

-.

.5.

I' ic', MIssili-,I rl, '2"! I(o1,l,, r) r I iL(: iIII d, 11,• L , 3-1 0 ROLL, is PITCH

4r 0 ,1 5' 1 111

"S..

S.:IIzl I lI ,, I I I

SFIGURE D-II. TUFT GRID PHOTOS IN AFT PLANE

"FOR MISSILE-1 Of FINENEbS RATIO 7.5

S 181--" :-''.2 :,i,,, -- ,,' ,'" ':3 :;:: ... . . . .". • - : --. . .: ,

......

[O•l,, 2O•2 din-! I1 MISSILER I 1i 3, ii MCI, 20 I• I I

1 Ia IS 1.k I I RO , ? )I C

m I, I II I. ii, ['m ,, I C) PITCHl

R CUL U. I)1 1F LIF CR10 PHOTOS I N AFT P LAN LM I II1. I . Of V I NFr[SS R AFA 10 /.5

?*''•: [1 ][ E]•' [][rL1[] ] :] L~ [ []L• ;l I e•Ilk y r181[j

hhAH. I sII 5 ak 5 1113

'.4

I, ... V%,•L=.,r•mr

h14.. MISSILE 111, 0 0 ROLL, 10 0 PITCH 1.4d. MISSILE 111, 0 0ROLL, 25 PITCH

I ' Ab2'

14b. MISSILE 1I1, 22 ROLL, 1O PTC 14lt. MISSILE 111, 22- ROLL, 25- PITCH

Al..

"4cb MISSILE 1.11, 45 R01,1, 0 lo" 14f. MISSIIE Ill., 45 -+

FIGURE 0-14. TUFT GRID PHOTOS IN FORWIARDJ PLANEFOR MISSILE OF FINENESS RATIO 7.5

184

0°

15a, MISSILE 111, 0 ROLL, 10 PITCH' 15d. MISSILE 1II, 0 ROLL, 25 PITCH

I..l r &

~~ 44

00

+?++,t15c, MISSILE, 111t , 45o RI tmh to° PI.TCHI.S�,LI 2ROL1l5.f, MISSTLE IL[ 45 ROLL, 25 PITCH

+,FI.GURE U-15 TUFT GRID PHOTOS IN MID PLAttES'.,.SIL.ltFOR MISSILE OF FINE'NESS RATIO 7 .5.

4418

I 4•

+ ' -. } i • • • , t . + li " ' i " I * I 1 ' l ' + ~ + " I " + I l I- l I • I" . +." + i +it + i +

4L

16a. MISSILE 111, 00 ROLL., 10 PI'fCH

Ill

16b. MISSILE 111, 22° liOm to PITCH

16c., MIsSIII: 1 , 45 oII.,, I1, Pi'rcii

FIGURE 0-16. TUFT GRID PHOTOS IN AFT PLANEFOR MISSILE OF F INENLOS kA 10 '1,

180

l7a, MISSILE ILI, 0 0 Ro 1,L, 150 PITCH 17b. MISSILE 117, it10 RO'LL, 15 0 P ITCH

17c~. MISSLE ILI, ~22 ROMLL, 15 ) PITci l7(. MI.SSI1YIl~t, 33l0 801., 1 ̀ PITCH!

2.F IUURL U- 17( TUFT UfR 1 U PHo[ Ob I N AVT Pt-Afr.'.:~.FOR W%'I ILL 01 F INM ) kAIl 10 j

18 a. MISSL.,E Il, 0° rL,, 20° PITC , MISSIHe IIIS, I1 ,OI.,, 20I PIT45P

t, MSS,•tl~ I. FI, 220 ROLl,, 2 Pl'lU 1d, I* ],,, Ill 330 rOl., 20M PITCH I:I;

I' * N ISS IIh IIl, 45° RO~l,, W0 I'ILC(II r

',,4

F I GURL: U- lHJ. JUF- [ GRID PHOOU~ IN Al- I PLAI',L ',

FO• MIl I Lb: OF F INENI:LS5 I? Al 10 1.J":

- 4

I'*1

op

lMISSIL Ill, ? o 1ll., 1. P 'ITCH. M SlII.i HI I I''' RUI, PITCH

I !rl 1-s ITC 1 1)1 Iý I't.I I I' I T " P0 .1 1I C

.V I .I t

. ...... ..

4(11

IIf

(i UR L2 . LU 20. 1 (1 1 hI k I ' IJ Pi I- 1 !, 1 O AN~ D PL A NA I I

ai

*L I 1

Mt ISSIL.E Ill.•{' Kill I, Jl 1)'I111 ,1 , v1: 1,11 NIINI.I II } q I, .,u lltll I'II •

S , 1 t II I l" l.rI

4 [i

FIGURE U-21. TUFT GR IU PHOTOS IN MI U PLANE

FOR MISSILE OF FINENL-'5 R~ATI 10J 0

I I]

.4--_. . , I .J ,] [ .i I --

FO MI b IL - 'IILf1

4�4

4*

'.4.

.4.14,

B'.-q

23u. M1�;SI I.I� IV, oO ROIl, 1 PIT(�1I

.4

* ,4,

44

04

4

1%*

*14

4�4

* � t�tJi�L Li �3 II! 1 1 .iIi PII�fO� U A� I P1 �

:1I 'I

,444.�

- - A 4 4 4 4 '44 '4.1

2a MLSSILE 1, 220 RoIL, 100 PITCH 24b. MISS11, E ! 45C Holl i PITmt

24d . " M I S'S11 K1 4, 5 R• 07• 1. 1, 1 r ci

I OR 1ý; !.', z I L 0_1 (J A I1

'1t4

14c , M 1S•[Li 1, 2.20 RO~l , 150 PITt~i

rid g tPl [;rI:li~ [•, 4[O RO l, • ' ]

F IU.Uh L~- U-24 , ItW.T CftI~IU P~IOT0O, I' Al I [ i'L.AI,,,L

,+, M I lL L 0! F I Nt. ~i L>j ' ,A I I0 ,l . .. ,

i I a iI I I

I I

2.$a ,* M I MS III,° I, 21?' I0)I.I., .* • I l''I { *•1, ,H •, ' .I I, .,2' F!• .. • I ''I

* *1 , H IS f .l : I , ,, ' Il II.I., ", I' IT " II

i"Si

"ii'. .•I ., I' II A t,

A : , ' : ( ) , ,, I{', ' (~ I , B I f • ; 1 ' ' A I il l I

-,,* ,-- - *

4°.

26a. MISStLK 1 0 0 ROL, 30 PITCH M6 ISS.I IX I II ROLLh, I30 PITCH

•26c . lS g LPK 1, 2, ROILL, 3o° PITLCII 20d, MISSILE' t, '31° Rj mh u0 PIrc I I

'It

a.Y

206O L, 1 SS 1V011,. I I , 4 53 ROM3, IO 1 , 1'I O'If

Io U R I' U.) 2t I[ .D I 1 6' A .f V 'F~~.•: OH NI V IINAI I0

*t,

* . " . ' " " ' ' - .'2. ' : : i . ' ' : . - . ' ' . . . " : " ' : " ' 'S.4 .. . . ."'- - ; " ' , • • " • - " " : " • . • ! I } ) - _ . • • Z . ' • L _ -

4.1

27a.MISIi 2, 00 ROL ~PTI 21 ISL ,~UROI.L, 30' PITCH

27c. MISSILE 2, '22 Ro~Lk, 3o PI1.TCHI 27do Sis S I 11 E 3'3 R01.1" '10, 1PIT7cH

I~t M ~U~ i~ /, 1, I S", 1,1- 4 1 W P ITCH

I i U,~ 1.1 i: 4 j 1 1 ,110 1 0Al

28a M ISS I S I.,E 0 ROMi1, 30" PI'TH 9818. M IiSS I I.' I, I1° tOll., 3Q0 PITCH

8 Xco m I S I 1." ). 2 I I., '1(Ro . i I' !-IT IH 28,1. M S" I ,lk 'I, Vi0 I .11, .t3) l'l'tc ll

., <, l i I ,. i j ( i . ,'i) P I(i A

I Sj

=,.

29a. MISSILE 4, 0 ROLL,' 3O PlIC 1.9 MISSILE 4, It ROLL, 30 0 PITCH

29c. MISSILE 4, O2 ROLi" u0 PIT'C i 2%b. MISSfLF 4, 33 ROLL, 30 PITCH

'4

29e. t M2 ' ii•S ik 4, 4r5l 2N0I11., PI TCH , 30

SFGUE- IU UP [R GP ID P[ 10, I N AFT PL ANr

FOi' MISS I, Of I ktS I T , 10 ) b 33

I tl-W

.J44

-'-I,~,+m U "

30a. MISSILE• 3, 0° ROLL, 300 PITCH

.111%

TIi

S~FIGURE D-30, TUFT GRID PHOTOS IN AFT P•LANE

:..,FOR MISSILE OF FINENESS RATIO 15,33

"4',' 0

r 4 •- - .

S .• • • - * o ., , -- a . - , , 4 ".. "° ~ " 4. . . ° I' ' I . . . o* . -, ..* , ., *.• . , . o*,•. . ,,%. , . •.

APPENDIX E

OIL FLOW PATTERNS

Oil flow tests were conducted on missiles of fineness ratio 8 and

16 in the subsonic wind tunnel at a freestream velocity of 360

fps. Photographs were recorded of the oil patterns for the mls-

siles tested at various configurations and orientations and are

illustrated in Figures E-1 through E-41. All tests were con-

ducted of missiles without fins.

Oil flow teots were conducted as follows. After painting the

models black, a white oil 'mixture of titanium dioxade, oleic

P" acid and 90 weight transmission oil) was sprayed in a speckled

"pattern on the surface of each model. The models were placed on

the sting, and the wind tunnel was run for approximately 2

minutes--the time required for the oil to migrate over the our-

face of the models. Photographs of the upper, right and left

aides of the models were then taken for the various missile con-figurations and orientations tested.

IPa For missiles of fineness ratio 8, each of the 4 bodies was tested

with the blunt nose at 10, 15, 20, and 25 degrees pitch and 0,

11, 22, 33, and 45 degrees roll. The 201 corner radius body was

also tested with the pointed nose at 10, 15, 20, and 25 degrees

201

pitch and 0, 22, and 45 degrees roll. A test matrix of the vari-

ous missile configurations and orientations is shown in Table E-

For missiles of fineness ratio 16, each of the 5 bodies was

tested with the blunt nose at 30 degrees pitch and 0 and 22

degrees roll. In addition, the 20% corner radius body was also

tested at 30 degrees pitch and 11, 33, and 45 degrees roll.

I iNTable 1-2 shows the configurations and orientations tested for

missiles of fineness ratio 16.

Figures 3-1 and 3-41 show oil flow patterns on the top, left and

right surfaces for the various missile configurations and orien-

tations tested. Each of the three views (top, left, and right)

of the model are defined looking upstream. However, at the com-

pletion of each test to facilitate the photography, the models

were rolled 90 degrees and 180 degrees prior to taking photo-

* graphs of the top and right views, respectively. To help slim-

inate confusion, a schematic of the oross-flow plane during the

experiment and during the photography is shown on Figure 3.01.

0W2

SI,

%it

[•'*.. . . . 6 ~ ~ 7 -. . .- .. .. . - .1 . .• . , .. .. .. . . .

g TOP cROLLO 10 O10

4 .. U5"jDLEFT LEFT RIGHT

MIGHT CAMERAA A

DFigure 2.OIA. Figure E.0103.

Position of Model at 11 Position of Model duringDegrees Roll buring Photography of LeftWind Tunnel Experiment Side (0 * 0 Degrees)(• • 11 Degrees)

:.T O p lowr A,•

.4P

"o RIGT D .

OA.1'-,,00 TOP R:16I% 1GHT LIFTC> % j CAMERA *%%CAMERA'-- % .a AIF Top

Figure 2,01C. Figure E.O9 D.

Position of Model during Position of Model during* Photography of Top Photography of Right

Side (0 = -90 Degrees) Side (0 - -180 Degrees)

"Figure E.01. Positions of Missile During Wind TunnelExperiments and Photography. View LookingUpstream (at Aft End of Missile)

203

.4 - . .'4. . .y......".. "4 .". . . . .4"

0 0 0 0

I.I

i! ,4I- 4 14 1. .M' W54 W 0 4 0 4 14 ý -4 ý4 0 4 ý - 4 0 4

t20

*I1

•4)

I

I. 4) fp

U3

* U'I a'4

*I "oo

H m.- 0 0 -Z4 ý ý- H H w00.4 04 P4 1- H 'Ii

205

SA , 6.4

in,

SII

r..•

S--I I

MUM I..

_E A

Iw

nin. A'•

• 206 "

*1.Rol I

Ii., PICrURr A- RIGH SIDE vitrw 2a. PICT1JRE D- SII PI:d

mal .1~ Roll ARAll

VeW. -~

Fb Pc~uRE 0-1 OIH ILE FLOW 2b.A~ZMO PITPHOI;- TOGk'AtKl

2 Model

'It il

Rol.. . . .. .O

AO vm 0

M ar p

A11

Ia. P1~M . ID s I. PZCM'i D- LW IDE qwm

(AllIM I MlY E. I P' RN .1 NP AA A0

FIGUE E-, OL FLW VSUALZATIN POTOGAPH

208t

MO, 1 ' MODEL• "R ot ROLL• :' A O AOA do'

Sao A- 'm

'" •1~~I. MO'IIUWD~l•Iml ZUWW*;i • r2a. PICZI3 D- WT SIDE VIN

lb. Plt=f 16 low slim VIDI 2b. PIC=l~ E- RIQ~T SIDE VjEw

MIODEL M MODEL IROLL ROLLAOA AOAV IE CVE I,,

1 . !p"I lm I- RIG(5 I Dr, kil Eb, %11•[ , •GT .. w\rZ

209

=A. .'. ..

4. RO . ,*' RO- ., "" .

lMODll ,

AO A"

I', , - . , ,

~ -

lb. P!IC I 4- ur1Q SIN VWI 2a. P "1"CM D- PJGDr SIM VIEW

MODELROLL Rl AW,ADA •'A0Ai,',.

MODELROLL ,,

AOAr V R I A

FIUIJRE E.4. OIL FLOW VISUAL/AIZIA1N tItIIUTGRAPS

210

I", , •

Pal ADA" ,

la. PIC=T A- IT SIM 1VIR 2m. PIC1NI D,. LW S1 VId

--i

. nma"; so t2b, Prct¶ICKU K- RUI'I HtiE VIEW':,i t~~b, Pl•'cm B- RI•I(" SIM yltv

FIGURE E-5. O1i. FLOW VISUALIZATION PHOTOGRAPHS'2

•I,

211

.1

MON IIIMAI

RollRO ILAAOA

'AO

1b, PICTMR 3.- IU SIDE VINJ 2b. PICZWM 1- ZITW SIDE VI~w

Ic. P~ICTUREC- IDIPSIDE VIM 2c. PIC=JR F- TOPSIDE VIEW

M~IN I. M I SSI IJ'ý 1 2 2') ROLL, 2T AOA ~ XL~JMISMI IE 1, 3311 Kolu., I ill A

FIGURE E-6. OIL FLOW VISUALIZATION PHOTOGRAPHS

212

MOD( tMODEL I

U1. PZC'TUZ A- LXYT SIME VIEW 2s. PICIM3 D- L'ff SUDE VIEW

AtROLL ar

AQA

FIGURE E--7 OIL FLOW VISUALIZATION PHOTOGRAPHS

.2 1'3

ub. P!cmW 3 r d= vn u. pzn~E.3Xu D- ~ uw =WI

IVI

1c. NZCRfl C- 'tUPS!DE VIM2 rVF _ rND l..

FIGURE E-8l. OIL FLOW VISUALIZATION PHOTOGRAPHS

214

'4

w,

IS. KCID= A- IVX 8=~ VIDI 2a. Pic=U D. DT MIXS VIEW

IA.

lb. PICM 5W ln M VIEW .2b, zICP F- RIu4T SIDE VIEW

.4.

• 71t INM - - -(V A( (O M NI IO •.'I' .. ' lI, N)

K.

4,.

S" .

FIGURE E-9 OIL FLOW VISUALIZATION PHOTOGRAPHS

215

. .

I -1 . * . v . ..

...

AOA ' 2,,. ¶ - 3 oll a* _ • : AOA tar'.;z

U., PIMSMR A-. Mi SIM VZIM2.FCnmu D- LM'F I= vil

,i,

Ruql 0

Po~ ii~i.c lls~ \'I .. icm~i.r i•'l.r ,!','

Vi ADA• /1o

•" •FlbI PIC= 5- EX1O. IF=U VIEWt 2b. P OTOG t- RIA P ICS VI

* .. 'a.. . .

;•'•+'- "•'U V-. Aw l AoA V i i

HUM *. 111 #L- .

f X lll I. M 1Y IrJ 1, t I P', 11.l., 1 A , 11.".', C)" MI I., PC A(*

," ~FIGURE E-10, OIL FLOW VISUALIZATION PHOTOGRAPHS '

S'2 1 i-ý

.a ... ...

lb. no=M b.p3 l ab. non s. lu- iza vim

AOAA

V w

Ic. PIC=t3 C- 'TOPSIDE VIEW 2c. PIMK - 1UPSriz VILW

=ML~t I. MISSI IJo I I, ' KOH I.. 2W' M~A M~lI' M I SS I IF I I~ , 4W.KOH . 10 Ai A

*1FIGURE E-11. OIL FLOW VISUALIZATION PHOTOGRAPHS

217

L+il MODEL IL . ROLL•:..e A ." +'ADA -',

ROLL

" 11

+-

MOE MODML i

9,,

LIi ,' ROLL Roi

VIE , A ,,' O <

I . PlIC=i 0- l VIM 2t. (ll(InrI(F. I- 1NIMU . \l 1 ri W

(JNIlt I. mitisllk: 11, 1, MI''N ., P V," NIA1 I MUM I.'j.41,111-: 11, li" R11.1

sDFIGURE C-2. OIL FLOW VISUALIZATION PHOTOlGRAPHS

218

MOPI

ROLL

*IEIo J. AA

4Vi

MOM[ : -

AOA A. ,AODA . .... .

N _lb. PICMtl b.. R1Ci 1= MW 2b. PtIMM Ito- MWICf IlgM YZDN

AVA

An

1c. PI MIR C 2RLD VIE U F - W K =I VfLV.VNi l I Il AI,

F ,.." : * * " * P

FIGURE E-13 OIL FLOW VISUALIZATION P'!OTOGRAPHS"

.., .' .- - - * ' .U ~ U I* U * * - N - - ; + . • . .

'Ni

'4O

I"w

AOAA

1o1. P1CT1 m C.- 1i5Z j= 2c IP- -TPII VIV.

(~U't *M~'i A I 2"HlaI~" ~IHI2, M~IA II wm'Hpl,. I&

FIGURE E-14. OIL PICMM VIUA-ATO P TTORPSI4SV1E

220

MIODELROLL .3

VIEW

I A.0

I&* =1112Z A- ULI MI VW1 2. pIOMm Ni LWI' 5an YM

MODEL

lb, PICWflD b-IN sim vZW PIC= Itnm- AUFSZIMvTN

MOD IIB

ROL

F-*')NN I

1. M I!; I LP 1 ,?"4lAA I 1 i I~ lý t 1 o.,I" N

FIGURE E-lb,. OIL FLOW VISUALIZATION PHOTOGRAPHS

221 .

I -M OD O[L N ODL N

ROLL ( . LL W

'mU'

* I,

', ... I 3-•- -.Sv ~~ROLL ,n:.,

a 4•":'ADA lot

1b. MCIl= t-aUZ o t V1hW

,.4:IM•NIL I, 3 I , 0 a At, 2 MI• 4I• I• I , ii'' WI. , ?'.I '

AA.A


222

!1 * .* *¼. M ODE .. M ODEL

4, "*' R OL -.

vie AlI i '

9-, . .

K- a

"lb. PIC= ws vz. C'Dbl Ir T IkI VKII

.:.'C-1114 F-, '101rill) VIN{€I' i V

9.,

"~C ll..+,.i VIM

.',',FIGURE E-17, OIL FLOW VISUALIZATION PHOTOGRAPHS

u223

!I;. I A.i., mvr

AII

SALIA D. UWNT v

AA

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