new limitation change to from authority · d projectile reference d&ameter ia axial moment of...

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AD NUMBER

ADB022223

NEW LIMITATION CHANGE

TOApproved for public release, distributionunlimited

FROMDistribution authorized to U.S. Gov't.agencies only; test and evaluation; Jan1977. Other requests shall be referred toUS Armament Res. & DEV. COMD. Attn:DRDAR-TSS Dover N.J. 07801

AUTHORITY

Per USAARDEC ltr 23 Jun 1989.

THIS PAGE IS UNCLASSIFIED

,%r

COPY NO.F -TECHNICAL REPORT 49f1

a COPY AVAILABLE TO COG DOES NOTPERMIT FULLY LEHILE I I 'U C,

AERODYNAMICS, DIMENSIONS, INERTIAL

PROPERTIES, AND PERFORMANCE OF

ARTILLERY PROJECTILES

HENRY E. HUDGINS, JR.

!ANUARY 1977

• ~ ~ ~ ~ ~ T 'Gv -m,.n :.:_ .:_ ^ to .. . . A~ge.n1cie•. offly (fes n•!. • l.

ation; January 1977). Other requests for this document must be re.ferred to I1

Q_ LS Army Arni.merit Peso &" l)cv Couid.Attri: I)[DAR-T-iS

S.[ov,•r, N. J. 07801

LQJ.___j

PICATINNY ARSENAL A

DOVER. NEW JERSEY

. . . •. , •. -,..,. . • ,: . ~ ~ . •.. • ..,•. - •-•,.. • ... ••• a l'

The findings in this report are not to be construed

as an official Department of the Army position.

DISPOSITION

Destroy thi.s report when no longer needed. Do notrvi.uit tv thte urigIinator. C

/a,

¢2'.

SECURITY~ CLASSIFICATION OF THIS PAGE (Wh-~ bet. Ent*1.d)

REPORT DOCU92NTATION PAGE aEFORE COMPLET1ING FORMI. RLPORT NISE 2 GC.VT ACCESSION No, 3. RECIPIENT'S CATALOC NUMBER

Technical Report '4911 -

_AERODYNA S _DIMENSIONS, IjNERTIAL,)________

9 4-ROPERTIES, AND PERFORMANCE OF S, 1EF MayR NUMBERobc

,ARTILLE RY PRO.JECTILES7. LIHOR( a aeGRN UBR.

/ D ----- AMG~ C4oS(qeVHenry E. udgins, J7 672701.4'2.H-93H1-8.01

P- ERFORMING ORGSANIZATION NAME AND ADORIESS 10. PROGRAM CLEMENT. PROJEFCT, TASK

Feitrman Research LaboratoryPicatinny ArsenalDover, NJ 07801

11. CONTROLLING OFFICE NAME AND ADDRESS I' EPOR L.AL_

Massachusetts Institute of Technology JanM E77Lincoln Laboratory. PO Box 73 04 .NM

ITM-NiZTVRIf0AGEN"CY NAME A AODRESS(lf diI.f1-.tI frm Cmt-CMI1og 0111c.) I5. SECURITY CLLi.SS. (.f ttle 1.pfto)

- Unclassified

1S. DISTRIBUTION STATEMENT (of MS. RopoI)

Distribution limited to US Government agencies only (test and evaluatiur;January- 1977) Other requests for this document must b5e -reTerred to P

US ARMY AaRMAM8,NT 11"S. DEVO COMIJ.Attn: LURUAA-*ThS 4

I- flISTRIOUTlONS4 f~jkvT re. Dover, J~ . 07801

DimnsinsDispersion Firing tables GuidanceInertial properties Sensitivity Lethality ProjectilesPerformance Zoning Vulnerability Artillery

NANIT'AACT (r-Wllo At WO.- .d 1 1 St~y br b.-k,WFWýJ)

-'he best available aeroballistic information on currently fielded and in-dlevelopmenUS Army artillery projectiles (1 05mm and up) for indirect fire has been collected orgenerated and is discussed in the main report. The aeroballistic data includes:dimensions and inertial properties, zoning, compacted firing tables, dispersion, sen-sitivity coefficients, aerodynamic coefficients estimates, and a bibliography of lethal-ity and vulnerability. A bibliography and available data on guided lrjcie

D D " 0 "~T mQ u -n o w n o r 9 o r.S i~s o e w L ~ v i

U73 UNCLA .,FIlED%LhCEJN'TY CLAMSFVCATJt M4 IU TtlS PA12 (U11.-. DIN. Entm~d)

I IN A--1 = F-- - - --I-

SSECURITY CLASSIFICATION OF THIS PAOE(Whhm Does 19PEW040

,": /20. ABSTRACT (contd) vie,

- aerodytiamics is also presented. A similar effort for Soviet munitions is reportedin the addendum to this report also includes classified data on US weapon

systems.

3

UNCLASSIFIED

SECURITY CLASSIFICATION OF THIS PAQ9g(u1. 0.1. DOM

!)

I,,ACKNOWLEDGEMENT

Many people coopera ted in prc ,:ding tne ir ,f'-mation collc rted inthis report and its addendum. "he major contribL:tors by o-gi.nizationwere: Aeroballistics Bra,-:h of the Feltman Re' t.arch Lab, ,ratory,Ammuntion Development and Engineering Dire ,-to-ate, Nuclear Develop-ment and Engineering Virectorate and the Foreign Intellgence Offce,all at Picatinny Arsenal, and the Exterior Ballistics Laboratcry of theBallistic Research Lanorztories, AMC Foreign Science and TechnologyCenter, Yuma Froviny Grounr's, the US Army Field Artillery School,and Edgewood A.senal.

. . . . . . . . .. ...JJ.. •

/

b

-

III

NO MENCLATURE

A projectile reference area, n d2/4

a speed of sound

CG SPIN73 label - center of gravity. calibers from nose

C 2 rolling moment coefficient, Q/1/2pV 2 Ad

CLP SPIN73 label - see Lquation 6

C pitchin. moment coefficient, m/ (1/2pV 2 Ad)m

CMA SPIN73 label - see Equation 3

CMQ SPIN73 label - see Equation 3

CN normal force coefficient, N/(I/2pV2A)

C yawing moment coefficient, n/ (I/ 2pV 2 Ad)n

C ' Magnus contribution to CnS n

CNA SPIN73 label - see Equation 2

CNPA SPIN73 label - see Equation 5

CNPA3 SPIN73 label - see Equation 5CNPA5 SPIN73 labei - see Equation 5

CNPA[5] SPIN73 label - Magnus moment secant slope per radianat 50 total angle of attack

CPF [11] SPIN73 label - center of pressure of Magnus force,

calibers from nose at 10 total angle of attack

CPF[bj SPIN73 label - center of pressure of Magnus force,calibers from nose at 50 angle of attack

CPN SPIN73 label - center of pressure of normal force,calibers from nose

CX SPIN73 label - zero total angle of attack axial forcecoefficient, see Equation 1

C axial force coefficient, X/ (1/2PV 2 A)x

CX2 SPIN73 label - see Equation 1

CYPA SPIN73 label - see Equation 4

C Side force coefficient, Y/ (1I/2pV 2 A)Y C" Magnus contribution to Cv y

At."

d projectile referenCe d&ameter

IA axial moment of inertia of p-nje'Atile about Fxis ofsym'.etr'y

transverse moment of inertia of projectile anout c.g.

IX SPIN73 iabe' - IA

IY SPN73 labeý -

L projectile over-all length

2. rohling moment

m pitching momert about c.g

M Mach number, V/a

N normal force

n yawing moment about z.g.

p zipin rate

P r,on-dimensionel spin rate, pd/2V

q pitch rate

Q non-dimensional pitch rate, qd/2V

r yaw rate

R non-dimensional yaw rate rd/2V, or range

V flight velocity

W projectile weght

X axial force

Xcg axial distance from projectile nose to center of gravity,calibers

Y side force

( total angle of attack

p air density

TABLE OF CGNTENTS

;-l U-O,.jUCtio F, Page No .

D;scjssion

AerobdIlistic Charactcristics 1

Weapon-: and Projectiles

Projcclile Dimcnsions and Inertial Properties 5

Zoning 5

Di.zpersion 20

Aerncynamic Coe~ficients 24

Trujectories nnd Firing "les-25

Contrcl Ae,'ooallistic 3 26

T er rm ii al Ballistics27

Lethality and Vqllnerabiiity 27

Sensitivity Coefficients 28

Conclusions and Recommendations 31

References

32

Bibliographies

1. Control Aerodynamics Analytical Bibliography 35

2. Control Aerodynamics Experimental Bibliograp' y 363. LetChality and Vulnerability Bibliography 38

i

Ktj

Append ixes

A Compacted Firing Tables or Simulations 55

Tables .

A-1 M30 mortar, 4.2-inch, firing M329A1 57

A-2 M30 mortar, L4.2-inch, firing M329A2 (M329AIE1) 60

A-3 MI01, M101A1 howitzer, 105mm, firing MI 63

A-4 M102 howitzer, 105mm, firing M1 70

A-5 M102 howitzer, 105rmim, firing M548 77

A-6 XM204 howitzer, 165mm, firing MI 83


A-8 Ml09 ,o.itz.r, 0 55mn-, fi;r:, ,,,


A-10 M109 howitzer, 155mm, firing XM718 108

A-11 M109A1 howitzer, 155mm, firing M107 11II

A-12 M109A1, XM198 howitzers, 155mm, firing M483AI 121

A-13 M1I9A1, XM198 howitzers, 155mm, firing XM715-2 129

A-14 M109A1, XrAi.;8 howitzers, 155mm, f;rirg XM708E3 131

A-15 M107 self-propelled gun, 17Smm, firing 133

M437A1, M437A2

A-16 Ml10 self-propelled how!zer, 8-inch, 136fir. ig M106

A-17 Ml10 self-propelled h-,vitzcr, 8-inch, 143firing M424

kI• • , ... -. ... -•>•.• ,:_• .€.• ,• = , .... ...

A-18 M110 self-p-opelled hkuwi~zer, 8-jt.czh, 146firing XM711

A-1 9 M110 self- .-)ropeIled hovvt-'er. 3-inch, 147firina XM6SuE4

A-20~ M110 self-propelled hc~witzer, 8-inch, 149firing 'IM75.3

A-21 Ml110F2 self -propcli -d howitzer. &-.inclý. . 5:firing~ XM7'I

A,-?2 M1 1OE2 :,elf-propellkd itowitzer, 8-inch, 1581 i ino' (M 61. 3E4

A-2?ý M1iOE. seil-propelleJ ho-vitzer, 8-inch, 159f> ,ryj XM753

B SPIN7.1 `retV,;ted A,2rodynariic Coefficients 169

t. 4.-'- .nch M329AI without extension- 171,

` -2 4.2-inch M'Z9A1 wiz,- eAtension 172

E,- 3 4.2-ir.cn M328AI wichout ýxtensicn 173

B. -,: .2-i.-ich Mi28AI with uxtension 174

3-5 4.2-inch M3.10.i wit;huý.41 excension 1-5

E-C 4.2- 11 ch~ M335A1 w,ýi, extensioi, 176

6-7 ~4. 2-inch M32fý'A2 'A32,,A~r.1) 17,7

Li-G 105mmr Mi (VI!E) 178

F,-9 1O5mry %,60 tWP;j 179

13-10 1Q&,nm M60 (96% or sw~okeŽ) 180

3-11 3.5mm MC4, 131 BE 1{,rnok2)j 181

4.

B-12 105mm M314A1EI (ilium) 182

B-13 105mm M444 (ICM) 183

B-IP '05mm XM710 (ICM) 184

B-15 105mm M548EI (RA off) 185

B-16 105mm M548E1 (RA on, launch) 186

B-17 105mm M548E1 (RA after burn-out) 187

B-18 155mm M107 (HE) 188

B-19 1 55min Ml10 (WP) 189

B-2i) 155mm MI10 (Gas) 190

B 21 155min M116 (wht smoke) 191

B-22 155mm MI16 (cird smoke) 192

B-23 155rm tý.121, M121AI (chemical) 193

B-24 155mm M485E1, M485E2 (ilium) 194

'3-25 155mm M449FFI ICM) 195

B-26 155mm M449E2 (ICM) 196

B-27 155mm M482EI (ICM) 197

B-28 1 55mm XM703E2 (HE) 198

B-29 155mm XM70BE3 (h:) 199

B-30 155mm XM549 (RA, iaunch) 200

B-31 15Smm XM549 (RA, after burn-outj 201

B-32 155mnr, XM454 (atomic) 202

B-33 155mm XM718/XM7'41 (AV) 203

B-3'1 155mm XiA692/XM731 (AP) 204

B-35 155mm XM687 (blk can) 205

1-36 175mm M437A1, M437A2 (HE) 206

B-37 8- Inch M106 (HE) 207

B-38 8-Inch M426 (chemical. 208

13-31 8-Inch M422 (atomic) 209

B-40 8-Inch M424 (atomic spt) 210

B-41 8-Inch M404 (1CM) 211

III,,.C t I ,, •L I • ,..~

LI- ",L U go~1 l~Jv3LI I I-l ) %_ ot

B-43 8-Inch XM650E4 (RA, lau:;ch) 213

B-44 3-Inch XM65OE4 (RA, after burn-out) 214

B-45 8-Inch XM711 (HE) 215

B-46 8-;nch XM753 (atomic RA, launch) 216

B-47' 8-Inch XM753 (atomic RA, after burn-out) 217

B-48 8-Inch XM736 (blk can) 218

C Cannon--Launched Guided Projectile Aerodynamic Data 219

XM712 AD configuration 219

Figures

I (Not used in this excerpt from another report) 225

2 Pitching moment and yawing moment due 226to roll commanco

4k

3 Pitching moment and yawing moment due 227

to roll command

4 Pitching moment and yawing moment due 228

to roll command

5 Pitching mome-nt and yawing momer.t due 229

to roll command

6 Roll power 230

7 Axis system and sign convention 231

8 Longitudinal stability, M = 0.4, 00 = 0 232

9 Longitudinal stability, M = 0.4, I = 450 233

10 Longitudinal stability, M = 0.8, 4 = 0P 234

11 Loncgitudinal stability, M = 0.8, s = 45' 235


13 Longitudinal stability, M = 1.0, = 450 237

14 Longitudinal stability, M = 1.3, 0 = 0° 238


16 1'F:ching moment due to strake S5, 4 = 00 240

17 Pitching moment due to strake S5, 4 = 450 241

18 Longitudinal stability, M = 1.8 242

19 Axial forc_, 4 450, a = 0, 62 4 = 00, altitud& 243

-4000 ft

20 Axial force M = 0.4, 4 = 00, altitude 244S"1000 ft

21 Axial force M 0.4, 4 = 45, altitude 245

- 4000 ft

:3

S. .. , ... ,, ,-,. _ .-. . , =,• il~ i,<l • <,i,• ..... ...

22 Axial force M = 0.8, P - 00, 246altitude = 4000 ft

23 Axial force M = 0.8, 0 =450, 247

altitude = 4000 ft

24 Axial force M = 1.0, @ = 00, 248

altitude = 4000 ft

25 Axial force M = 1.0, @ = 45J, 249altitude = 4000 ft

26 Axial force M = 1.3 & 1.8, = 0", altitude 250

=4000 ft, 8 1 3 = 82 4 = 0I I

27 Axial force M = 1.3 & 1 .8, * = 450, altitude 251

= 4000 ft, 8 1 3 -82 4 = 01 1

28 Roll power, C , 4 = 00 252

29 Roll power, Cj, @ = 450 253

30 Induced roll coefficient, Moo 0.4 254

31 Induced roll coefficient. Moo- 0.8 255

32 Induced roll coefficient, M-o = 1.0 256

33 Pitch dampinng A 0= 257

34 Roll damping, C , a = 00 258Pp

C Cannon-Launched Guided Projectile Aerodynamic Data 259

XM712 ED configuration 259

Geometry and Mass Properties 261

Aerodynamic Properties 261

1i

pI

Figures

35 Geometry and mass properties 263

36 Normal force coefficient slope versus Mach number 264

37 Pitching moment coefficient slope versus Mach number 2 6 5

38 Center of pressure versus Mach number 265

39 Axial force coefficient versus Mach number 266

40 Axial force coefficient breakdown 266

41 Incremental axial force coefficient versus 267fin deflection, M = 0.5



44 Pitch and yaw damping deri,/atives versus 268Mach number

45 Roll damping derivative 268

46 Fin power in pitch and yaw versus Mach number 269

47 Normal force and side force coefficient slope 269with fin deflection versus Mach number

L'8 Roll power versus Mach nuL-iber 270

49 Trimmed load factor and CNtrim versus 270

pitch fin deflection

D Cannon-Launched Guided Projectiles RecommendedWind-Tunnel Test Programs

Canard-controlled fixed-tail design 271

;. i

Fixed-wing tail-controlled design 285

Distribution List 301

Tables

1 Currently active fielded projectiles (US) 3

2 Projectiles in development (US) 4

3 Dimensions and inertial properties of 64.2 inch projectiles

4 Dimensions and inertial properties of 7105mm p'ojectiles

5 Dimensions and inertial properties of 8155mm projectiles

6 Dimensions and inertial properties of 175mm 10projectiles, M437AI, M437A2

7 Dimensions and inertial properties of 11

0 inch projectiles

8 Zoning solutions - muzzle velocity (m/s), 12

4.2-inch mortar, M30

9 Zoning solutions - muzzle velocity (m/s), 131751 mmn gun, MI07

10 Zoning solutions - muzzle velocity (m/s), 141 55mm systems

11 Zoning solution, muzzle velocities, 175mm system 16

(self-propelled gun, M107, projectile M437A1, A2)

12 Zoning solutions, mu7zle velocity (m/s), 17

8-inch systems

13 Rocket assisted projectile thrust data 19

$~

14 Field artillery cannon-type weapon systems 22

15 Approximate relationship between squares 30and weight

Figures

1 Definition of quantities describing projectile 41geometry and inertial properties

2 M101A1 (105mm) MPI probable error firing 42MI HE projectile

3 M109 (155mm) MPI probable error firing 43M107 HE projectile

4 M109 (155mm) MPI probable error firing 44M549 RA projectile

5 M109A1 (155mm) MPI probable error firina 45M107 HE projectile

6 M110 (203mm) MPI probable error firing 46M106 HE projectile

7 M107 (175mm) MPI probable error firing M437E2 47HE projectile

8 XM712 ballistic and FUFO trajectory option, 48XMI98 howitzer

9 Shallower approach angle of FUFO compared to 48ballistic trajectory of same range

10 Ballistic trajectory maneuver bounds, 4912km nominal range

11 FUFO trajectory maneuver bounds, 4912km nominal range

12 FUFO range extension for XM198 howitzer 50

IIt

13 Maximum FUFO guided range, XM198 howitzer 51

14 Minimum range trajectories with M109A1 52howitzer, charge 4

15 Minimum range trajectories with XM198 53howitzer, charge 4

16 Trajectory flexibility due to FUFO and 54high/low QE options

17 Engagement probability, ballistic and FUFO 54

I

t.t

4~~*

INTRODUCTION

This study was undertaken to provide an aeroballistic data base forProject HOWLS (Hostile Weapons Location System) , an ARPA initiated taskadministered by the Lincoln Laboratory of the Massachusetts Institute o0'Technology. The term aeroballistic here is used in a very broad sense asthe study was initially intended to cove- both US and USSR projectilecharacteristics: dimensions and inertial properties, trajectories, zoning,dispersion, and aerodynamic coefficients; control aerobal I istics: experi-mental and analytical statusof spinning projectiles with aerodvnami,: con-trel ";:irftce' (especially canards); present and orojected fuze d.:mions;qun launch environments and hardenina capabilities (especially sensors);and terminal ballistics and effects: lethality, vulnerability, and sensi-tivity coefficients.

The tasks discussed above were to have been completed by the endof January 1976 (nine months from the starting date of 1 May) . Changesin FY 1976 funding for the entire HOWLS program resulted in LincolnLaboratory requesting in September that work be halted at that point andt11di Wn1diever had been accomplished tip to that point be reported.

In order to make this rep,'),-, more widely useable, it has been dividedinto a main report and an addendum. The main report contains no classifiedinformation. All of the classified information is in th,: addendum; this in-cludes some range information on US rounds currently being developedand all of the information on Soviet munitions.

The reprogramming of funds by the HOWLS Proj ec, sponsor resulted infunding being dire'ted to other tasks than this one. 'The cffect of this is dis-cussed where appropriate in this report. A useful data base has been createdwhich can be extended to its tull capability at a later time.

DISCUSSION

Aeroal listic Characteristics

Weapons and Projectiles

The main published sources of information on US Army weapons inuse at the present time and the plans for the future are References 1 and2. These references should certainly be obtained as part of the overallprogram.

I1

The indirect fire weapons currently considered to be active (somereserve units and US allies may still be using others) are:

1. 4.2 inch: M30 Mortar,

2. 105mm: MI01A1 Towed Howitzer, M102 Towed Howitzer(air mobile); M108 Self-Propelled Howitzer (only in some active NationalGuard and US Army Reserve units)

3. 155mm: M109 Self-Propelled Howitzer (conversion to M109A!expected to be completed by FY 1976, one-half had been converted as ofOctober 1974), M109A1 Self-Propelled Howitzer, Ml14A1 r'owed Howitzer;

4. 175mm: M107 Self-Propelled Gun (wiil be phased out when

M110E2 is available)

5. 8-inch: Ml10 Self-Propelled Howitzer.

The future mix of weapons is expected to be:

1. 4.2 inch: M30 Mortar

2. 105mm: XM204 Towed Howitzer

3. 155mm: XM198 Towed Howitzer, M109A1 Self-Propelled

Howitzer

4. 8-inch: M110E2 Self-Propelled Howitzer

The various types of indirect fire projectiles currently being usedin and supplied to the field for these different weapons systems weredetermined from a variety of sources. Among these souwces were:Department of the Army publications (Ref 3-17), Ammunition Dev3lopmentand Engineering Directorate (ADED) at Picatinny Arsenal, BallisticResearch Laboratories, Edgewood Arsenal, and the US Army Field ArtillerySchool. The results are shown in Table 1.

2

Table I

Currently active fielded projectiles (US)"

Bore size Projectile designation Type

M329AI High Explosive (HE)4.2 Inch M329AIE1 HE(Mortar) M328,6,1 White Phosphorus (WP)

M335A1 Illuminator (Ilium)

M1 HEM 60 GasMGO Smoke

105mm M60 WPM314A2E1 IliumM444 Improved Conventional Munition

01CM)M548 HE, Rocket Assisted (RA)

M107 HEMilo GasMilo WPM1 21A1 Chemical

155mm M485EI, E2 IliumM449, El, E2 1CMM549 HE, RAM454 AtomicM483A1 ICM

175mm M437A1, A2 HE

M106 HE

ML426 Chemical8-Inch M 404 ICM

M422 AtomicM424 HES

aThe corresponding available data for Soviet weapons and projectiles isin Table IA of the Addendum.

US projectiles not yet released or still under development are listedin Table ,

9 3K Io

Table 2

Projectiles in development (US)

Bore size Projectile designation Type

105mm XM710 ICM

XM70SE2, E3 HEXM718/741 AT (antitank)

155mm XM692/731 AP (antipersonnel)XM687 Bulk CannisterXM712 Cannon Launched Guided Projectile

(CLGP)

XM650E4 HE, RAXM711 HE

8-Inch XM509 1CMXM736 Bulk CannisterXM753 Atomic, RA

4 3

Projectile Dimensions and !nevtioi Ptec-perties

This section prcser-ts thr. best dat.7 c~irrently av..ailrile. Thleyrepresent cont.-ibutions fromn many sect"Jll, of Picalinny Arsena!, BallisticResearch Laboratorics, Yuma Provinci (roura ., ani 1-dg,:--wocd Arsenal.It must be realized that bct.,i production ano d.Žieliapmnefal projoctiles,change in these charactt~ristics. Maniy oý thc. tielsed ar,6 stoclk-piled pro-jectiles were ae'ieloped at a trrna whe,) close atte.ntk-ti 110 shzp~- and incrtialproperties was not considered n~ecessary anci tnerefore the ireaseremerntsavailable are both la~w in number and old (Ref 18l and 19) , rodL'C-tiotllots also vary in '*ese characteristics due both'o ru-mn-inv1 chancies r-adeover the years and! changes in the method of r 1a71_1faCtL rf- and of maoufacturer.The developmental projectiles are exactly that and, hence-, a! e suibJect tochanges in properties during the devLiopment cycle. iAt Of thl!F is iriaddition, in both the above cases, to t~ie normal dlevia~inns to be e~xper.tedfrom round to round. All values given ýre thý nomninal values

Wilh these caveats in mind, the p-. ojectile dimensions and inertiEJproperties are given in Table 3 to 7. The proper-ties listed are :is d-f-neýdin Figure 1. The tabulated dimensions are ail given in caliber!s ((ccflteC ofgravity is from the nose, where nose means the tip of the fuze and anexterior length of :3. ý'S inches; wdt used four thec fuzP1 except for thp. shelldiameter (DIA) which is given in inches. Weight is liabulated in poundsand the moments of inertia are in pounds-inches squared. A faw. Shellwhich are being or have been deleted from the inventory and, their eore,do not appear in Table 1 are included in these tables to prov-de a mot ecomplete data bank.

The data for Soviet projectiles are presented in Table 2A which is inthe classified Addendum to this report.

Ohngeab Tofe hears the nomenclature in this area used loosely and inter-chaneabl. Tobe exact, a "Charge" is a standardized amnount of a par-tclrpropellant which produces a desired muzzle velocity for the pro-

jecileandweapon under consideration. A "Zone" is the distarce on thegrond etwenthe range at maximum range quadrant elevation aod therag tmaximum quadrant elevation for a given charge, proj-ctile, and

weapo5

0 In '. N ~ a -

(N 'T 4N C-'o m C) I 0a(-j O-

411ID Ir 0 -4

CL r- -4 1,- - ) 0

L -~W ~n 00('J'-

C~r c 0 -CO -i 1 r Id1~C' -4 I*-

I- II C)'n-

co t4 LUI -Lnr-

x~ '0(N, CA r-)

a 4 '-4R E4 Un IE

X -. r 0'o -D

N (7'

ZN 0,

(N 0 r ,0

"co .rN 1n (7 n 0 0( '

en en oo" .0 * o.7$~ ra Id a' un ITI NO O W e~~~~ * - n -a '-N N>o.

co rnc oe -> o NO' . 0)4

.04w C0 0nN a

00 o

enc r N- m

Iq 0* r 0 (4 -

u)

0 ) tý co "rN.(

e. co 0 n 4

o~c m. 0n e

10 0- N

enn

I p- a' I--7 ~ ~ ~ ( 0 '- :L

C) --- C3 in n.IV ei

'-- -

N. ~ ~ ~ ~ .0Z; - 0 ' -'

(' "V UV 0 'n 0

CPC

0) ~mI ur- c-IN o'CO

I

'Ca 1�t II 'in 0- I

a- 1' n'-.r c-

ia C II j -0 in�'� Ia' a' -II II C, a'

S -'-�-�'- - __________Q' H Itt ( a'

CC '7i'. a'i'n I

Ia' .2� �K i�f-Iinc cC- dcv

�-t-o �

U a'

cOO inn '7'.

-� 7 V'-� Ii .2- *,c

U0 HIn

(U0- nr "cC

I-' I 0 ''0 0�li<I _TilL_.r''7 in ? 0' - a' 0 C� iCin 'in C"

a' a' a' cc. a' 0 a v o a' a a-" c-a icr i-ca'

a' in i-i a -r in 'a 3' (, Q 0 iDa no iic.'i 't

in CiCi in in 'V

£' CL

_________________ i�ic -'a- -"-'

9 A

I'

AI

Table 6

Dimensionz and inertial propertieeof 175mmprojectiles, M437A1, M437A2

LOA, cal 5.48

OGL 2.93

BTL 1.00

XCG (nose) 3.50

DMP 0.080

DRB 1.032

OGR 25.0

BML 0.00

DBA 0.713

DBM, cal 0.00

DIA, inches 6.885

(meters) (0. 1749)

IA, lb-in2 954.

(kg-m ) (0.279)

IT, lb-in2 11800.

(kg-m ) (3.45)

WGT, lb 147.8

(N) (657.4)

*See Fig 1 far definitions.

10

o T3 04 0'

0 NO 040 c I-.n o

77T ~iY0 C' 1:'3

".04~ 0 03 *

o CD 0 0 * o 44 C0

'M' x 043 0

Table 8

Zoning !§olutions - muzzle velocity (m/s),4.2-inch mortar, M30

CHARGE EXTENSION M328A1 r4335AI M329A1 M329A2(INCREMENTS) (M329AIE1)

5 No 109 110 108 NA

10 145 145 144

151 181 ].81 180

20 217 217 216254/8 No 255 253 256

25 4/8 Yes 229 230 227

30 250 251 248

35 273 274 271

41 Yes 298 297 299 NA

0 NA NA A NA.9I, A I

5 1I 1 40.6-,

10 178.5

15 21l., G

20 241.3

25 268.5

30 294.4

34 NA NA NA NA 314.9

M329A2 uses a different set than the others. Not allincrements are shown for both sets.

12"p~

'-4T

CD 0 c ' 0000 m ti) e Cu0 u'W 0 oýo (,I; r )Ma'. I OIT z z c C ZZq *0~ ('Lf ON (or OC4 L( `-4 N w I, zIn H C,4 (NCl' cq ,4 (- m m cr tnL O k Ln

0 4

r-~ , r-~ 0 kC'D t- c a o t-mNI a,.H m4 Q C~(ID I1 1 1 c~~~~~~c O' N-~r Oo- ~ N ar- c0 o o

kD r DC N0 C 4M M V% -It o I I-1 -4 4 - N NN M M N n m-Iv 1

x I

cnmI

iu'~' jm frI-U- LH -~~r 'mj LlC I I I 1--

'I-C14(4 (1 N N C'(

OO(4 OO N OO 4 OQ" C14 ' OCA ' c!Ct "

C-.4 1 HH (N C. , o

W- -' I -4 ;r 0

' -. I'-

13

I

4)

04 04 10

V 0 '0 0

04 04 .4,

04 OlIn 04 0404 0� 0404 04

04 0 0 ('

0 04 04 04 lfl 1.-I V 0410 V1< �004 N 0.-I 13 0410 In

10

040 04 NV V 04V In In N04U10 In10 04 VV N 0404 04 0104 10 0404 NIn 0401 04 0404 0401 V

04

04.-I'004

42E 'C 0404 04 V04

EU,>1. 04 .- � - o'� �LI*� 0, N1 N 0404 0404V00431 04 043' -in - 0404 0InC'CNOOInInIP

2 0 0404 040404 0404 0404 VK -Y---'f-�t----�t-04 IT �

I .1%

04c� -, 04

N 10

- 0404 V 04N .0404 In 10Q040404 V

0404 04 ON 04 VIP 0 InN 04 00 004 01.-I *1 0404 In NI� 04 �I�l '0 r I ICV 0404 04 0404 04 0401 04 0404 04 0404 V

0

L�L '� II IU, o0�C --

C N 0404 04 NP N 04V V 010 0 0404 In

0 -4 N" 04 OP N InN 04 N04 In

N 0 Q�1'01�I0��.0..INNN �0

- 1��

�04 10 �04 .0 �04 .0 1004 04 0404

10 0404 0404 0404 0404 0404 0404 0404 0404 0404 0404

'.. 00 0-4 00 0.-I 00 i-I 00 0.-I 00 0-4

01

04 -I 04 - a t�4.4 0� 4�04 04� fl,.� I*�

13.0 .0 II.

________________ ____________ I.0?

114

5.

-* - -... � .. �.- - -

V �'IRV�I'IddV JflN

02 20.fl V(N 4)0 (04) N 212(12 02 20.0.0

V(N 2002 0202 02� 02 02.4 U) Za 2NO) .- 2(N NO) (fl(N 02 1220 N 02(N(N mM (Nfl 002 In 112(12 '0 20

0 .�r- QO) 0202 .1202 0' V(N 0 020

212 NO) 2NV NO) NO .4 2-2-- 0 Z02 �02 (N (N ((2212 20.0 0202 20 12212 N V

'1' .2(N I

.4 I

'0(N I 'I02 IN V I

U)(N 0 U) 200)20 020 1202 N 0.-2(N212N 002.4'0o' 020 '002 0202 02 0202 20 7.20(N (N fir) fit') 0202 12 U)U) 20 V 02P �.--i7K�'02m920 1IJL�.

0

02

t -

(V0

* (N '0 � (N (N2 022, N 020 � 112'00) 2112 00 -412) 0.4 V '0

22- '002 .4(N' NO. .020 0 '0N 02 (N02 (N(N (NI') (N(N 0202 20 flU) 20 '0 02

7.

7. 2.3 111 ____ --I-.(N r-'0 O'O. V(N 0212) 02 002 - fi

02 (Nfl (N 002 012202 .. 4(N NO) 'ON 0 '020 02 7.0) 7.(N(N (NM (Nfl '0 4)212 '0 '0

N.4 -2 .4 - �4 .' a -4

0202 0222- 0202 .3202 0202 0)02 021) 020200 00 00 .4.4 00 0�4 00 0�4

7.7. 7.7. Zk 7.7. 7. 7.7.

1.2 -. - - .-. -.0 (N (N (N (N 0 (N 0 0' 0'0 �'( 7.� �.C � (N 7.*� (N -' (N'C (NV 402 4)02 WV 204' f-V N7. 02.-I 027

7. 7. _ 7. 2.2 7.

2.1 - .- - - _ -.- -I15 4

Table 11

Zoning solution, muzzle velocities, 175mm system

(self-propelled gun, M107, projectile M437A1, A2)

CHARGE MUZZLE VELOCITY

(mls)

IG 510.5(XM124)

1w 510.5(M86A1, A2)

2W 704.1(M86AI, A21%

3W 914.4(M86A1, A2)

16

A lo

r X0

0 r: - ý OCo a'ý1 o" t' 0oi (CJ 0-c a~W 0 )in :v -: Nr ý ONJ 'ý'l 0 r4 (N~ IT M fl Z't3 0'z u 2ý7

N JC\IN (11 N) 4CN mC' M '.ý', 1 Ln Lr)kD '0 '

E

in N- -4

7 J NN N0 M oi ( N

e~ n

(Ne ,-r- O L

I.- 1ý an 1'i inin M C-)'T 0 if 0)4 0I OO COl z m Z fl)

N Lri C1 (N CN 04 (N N Inr' ýT ~Ln A LnL in

N

0 (7) n 'IT 0 0 1ý 4 C a--I O 00 r- N -1 oN r ijCNY ýr n cO 0 4 ~ Ln -4 CN --4 'I m CoN mo ZO z 0

0C~(mNr~ 4'' -I ~Ln Lin Nto

o ~ ~ C m M Coi v~rC~ n n n oO ~ a

L on V 0 Cr 0) 0' v 0f ~ Cin Cod 0 N 00 0

CC7 ýr C'Jn (N(- (C C' 1 l' 0 Ln LA Nni N N

(Nc N ( (N (N -T (NT (N (N (N r

0 r4 0

C14~( (N4 N-4C1 l C4

00 .00 00 00 Co 00 00co0)

14 -1' - 1 rfý -1 -4 1-4 (N1 (N q (N -1 H 4

r-4 (N ~ rln ý LAn mE inD N- (3 Co-4 0I(3417

A Cha,-ge is usualiy also identified by a one or two character alpha-numeric code tor ease of referencing (firing tables, etc.) . Quite often thereis more than one type of propellant (the difference can be in either compo-sition or shape or both) used in the same weapon system. These typeshave an official designation also. For example, the 155mm M109A1 Howitzercurrently uses three such propellant types designated as: M3AI, M4A4,and M119. There are five different amounts of the M3A1 propellant usedand identified as Charges IG through 5G; five different amounts of theM4A2 propellant identified as Charges 3W to 7W; and the M119 propellanthas one charge, Charge 8.

A zoning solution for a weapon system has as its main goal theassurance of a range over-lap between the zones of adjacent charges or,at the very least, the avoidance of a gap. Quite often practical aeroballisticswill also affect these solutions since all shell have some Mach number andquadrant elevation regions where they exhibit lower performance thanover most other regions. A judicious selection of launch velocities canoften help alleviate the effect of such flight regimes and therefore decreasedispersion and increase effective range.

It can be seen that a zoning solution consists of a set of muzzlevelocit~es which, in turn, determines the charge (type and amount) for aspecific weapon and projectile.

These zoning solutions have been tabulated for US weapon systemsfrom the 4.2 inch Mortar to the 8-inch Howitzers in Tables 8 to 12. Theseare based on References 3 to 17 and data provided by Firing Tables Branch,BRL; Yuma Proving Ground; numerous sections of the Ammunition Develop-ment and Engineering Division, Picatinny Arsenal, and Edgewood Arsenal.Note that the 4.2 inch Mortar difters from regular artillery weapons in hav-ing only three quadrant elevations and many muzzle velocities (chargeincrements) . Thus, Table 8 has only selected charge increments. If acomplete tabulation is needed, they can be found in References 3 and 4.The zoning solutions that are available for Soviet weapon systems are inTable 3A in the classified addendum to this report and so is classifieddata on US projectiles.

Rocket assisted projectiles (RAPs) require more than their launchvelocity to be specified in order to predict their range and, hence, theirzones. Therefore, the necessary remaining information beyond that inthe inertial properties tables for before and after burning and the aero-dynamic coefficients in Appendix 13 are presented here in Table 13 for USRAPs (insufficient data is available on Soviet RAPs).

41

• 18

*

Table 13

Rocket assisted projectilc thrust data

Delay timea Burn time Thrust Drag form factorProjectile (sec) (sec) (Ib) (during burning)

M548 14. 2.3 92.5 1.00

M549 7. 2.5 558.0 1.00

XM650E4 7. 3.0 786.5 0.96

XM753 7. 3.0 786.5 0.96

a Time from launch to motor ignition

19

O II

Zoning information for the XM712 is also available from the trajectory

data in that section of this report and in the zoning section of the Addendum.

Dispersion

The US Army has standardized upon the probable error as themeasure of dispersion. Range and deflection dispersion are treated asseparate one-dimensional problems. Since a probable error in range ordeflection is defined as the distance on both sides of the mean point ofimpact (MPI) which together will include (in a statistical sense) 50% ofthe rounds fired, a one-dimensional probable error is 0. 6745 of the un-biased standard deviation.

These probable errors, range and deflection, are tabulated inReferences 3 to 17 in their supplementary data tables. They are also shownin the probable error columns in the compacted firing tables in Appendix Aof this report.

"Firing tab!e" values are usually the smallest measure of dispcrsior.Various other measures of dispersion are thoroughly discussed in Reference1 and the pertinent excerpt is included here verbaLiim. The only changeshave been to include some curves of the "firing table" values (these arelabeled "precision" since they conform to that definition in Reference 1) ontheir graphs and to adjust figure and reference nomenclature.

"One of the most confusing field artiilery performancecharacteristics is the delivery accuracy. Table 14 lists boththe precision and MPI probable errors for conventional andextended range projectiles. Precision is the scatter of burstpoints about the mean point of impact (MPI) of a group ofrounds fired from a single weapon on a sine occasion froma single site. The MPI is the mean range and mearn deflectionof a set of impact points. If the rounds are fuzed for ?irbursts, the mean burst height is also included. The MPIis not necessarily the aimpoint or target. The probableerror in precision is usually expressed in meterz, (m)measured from the MPI ;f, for example, at a certainrange 50 Percent of the projectiles fa!l between the meanrange plus 10 m and the mean range minus 10 m, theprecision probable error in range is 10 m at that specified

range. The listed precision errors are given in units ofpercent range (range at which measurement is valid) and

20

mils deflection. The values given are average values th;'.tmay Occur between 75 percent of maximum weapon rangeand inaxinmum range at the top charge. For instance, Table1it Iiý,ts 0.21 percent range and 0.65 mils a, thz! precisionerror for the Mi~lAl howitzer firing conventional munitions;3therefore, the precision probable error in range at iraximur.arange ('11.0 km) is 23. 1 m and the precision probablIe errorin deflection at the sam'Q range is 7.0 m. At 75 percentmaximum range (8250 in], the precision probable range anddclofction t_ýrors are 17.3 and 5.3 m, respectivoly. Thelisted pre-cision data are not applicable to ranges Iless than ISpercent maximum weapon range (precision error v's rangeis non! inaar) or to chi rg;2s (zones) other chan top cnaroy.ý

To describe a more -cal~stic delivery 3cciiracy, themean point of impact (MPI) error is used. The MPI error Isdefined z's the scatter of MPIs about an airnooint. The aim-point is not necessarily the targcýt, there may be an unknowntarovi loca Liof error-. Precision errors are cei7.ed primarilyby inherent errors in z single weapon and ammunition Syý"!:inrbut MPI errors are caused by system errors such as imperfoctaiming procedures and erroneous metcoroiog icM predictions.In a fire mission adjusted by' a forv-.ard observer, the primary-source of MPI error will be the forward observ~r's adJustmentand iocation inaccuro~ies. In the Met + VE predicted fircmission, however, the MRi erro,-, willi he citused by rnet2oro -logical errcrs (Mct) arci vtflocity error-, (\ffl" such as ft.ba-to-tube differences (iii a battery) arid registration ervors (aregistration is never truly accurate, but it is as-sumied to beýso: therefore, tihere is a constant reSidItZI error ior edch

registration) .The largest mneteorological error results fromithe inability to satisfactorhy predict wind velocity ;,nddirection. This ballistic wind error may be 150 percentlarger than any other singlc met error. Available Met + MI'!jprobable errors are given in Table 14 i i units of p--rcentrange and mils deflection. A-, before, these are aver-agevalues that may occur between 75 percent of maximumweapon ran~ge and maximium ranq:e at top charge.

Figures 2 through 7 graphically dlescribc th(! rangeand dcetlection MPI probable e;rror (in metres) as a furr tionof range for selected weapons fir;nq Met 4 'VE missions. In

21

c

Z~ <- <4<

c 1 -: .- <ri t 0 2 -

0) <

Lt'L C--

CL '

0 4)

co

.- x

Z -n

CL (v . '

22 4t)

rmos, illustrations several zones are represented and identi-fied by; for example, I (Charqe 1), II (Charge 2), and 111w(Charge 3, white bag). Several features of this se.ýries of

figures are outstanding. First, although low charges aredeijgr-,,qd for short-range operation, at certain ranges thelow-charge error is nearly double that of the top zone atthe same range. A principal cause of this phenomenon isprojectile instability due to slower launch velocities.Catnnon life expectancy is advantageously extended, how-ever, when lower charges arc used. Figures 3 and 4 sh('wthat the M109 firing the M5149 RA projectile has a smallerMPI range error than the M109 firing the M1 07 HE projectileat ranges above 8 km with Charge 7. At 12 km, the M109/M549 RA has an MPI range probable error at 74 m; theM109/M107 HE, 90 m. These values seem illogically re-ve.-sed. One possible reason for this unexpected resultmay be that the RAP is less sensitive to ballistic windscecause of tne inherent in-flight propulsion and improvedaerodynamics. Figure 7, the MPI probable error of theM107 175mm gun, shows the error magnitude that may beexpected for 30-km systems: range probable error, 20m;deflection proba)' ,error, 110 m. This is not the end ofthe delivery accuracy story, however, as best shown bythe He!bat I tests (Ref 20) where simulated operationaireadiness tests produced some errors gretly in excess ofthose given by the MPI curves: for an M109 howitzer firingto an average range of 9.0 km, graphical range probableerror was 135 m and deflection probable error was 86 m.The MPI prohable errors for the same range and zone areas follows: range probable error, 85 m; deflection probable"eror, " ,•l ua fro I toJ 2Lerror, .3m. Since the e I'l L- ranges .aried fr, m I to 12km and since all Helbat missions were riot strictly Met +VE types, a direct comparison of the Helbat I data with theMPI error curves may be questionable: but the effect oflh.umarn error ouviously should not be ignorcd".

Further discussion of thiv. topic may be found in Reference 21.

For any case in Appendix A wher e the source is not a firing tableand probable errors are given, they are either from a limited number offErings or estimated from computer simulations. rhese values should beconsidered as estimates only. It i5 worthwhile to repeat the warning in

23

I

the discussion from Reference 1 about the dominant effect of meteorological

error, primarily winds at altitudes, upon precision and the importance of

target location error upon actual miss distances.

The only guided projectile considered in this study is the XM712

(Cannon Launched Guided Projecti!e (CLGP). The discussion of its accuracyis given in the classified Addendum of this report. Dispersion data onSoviet munitions w iclh is available is also included in the classified

Addendum to this report.

Aerodynamic Coefficients

All of the aerodynamic coefficients presented in this report, except

for the XM712 (CLGP), were estimated by the same method and are pre-sented in the same format. The method used is documented in Reference

22 and is available as a computer program, SPIN73, in FORTRAN. Itconsists, basically, of empirical curve fits to a large data base of the effect

of various proje-ctile dimensions upon the aerodynamic coefficients (Ret 22)

"The estimates generated by SPIN73 are given in Appendix B, exceptfor the data on Soviet ammunition which is in the classified Addendum.Some discussion of the meaning of the various column headings is neces-sary to understand how to use the output in standard aerodynamic co-

efficient form.

If we call the total angle of attack ca (radians), the spin p (radians/

sec), and the angular rates are pitch, '4, or yaw, r (both rad/sec), then thevarious coefficients are, in terms of the SPIN73 tabulated names, as afunction of Mach number:

Axial Force: Cx (M,a) =CX +CX2 sinsa (1)

Normal Force: C N(M, a) CNA sina (2)

Pitching Moment: C (M, a,q) =CMA sina + (qd/2VjCMQ (3)

Magnus Force*: C' (M,a,p) (pd/2V)CYPA sina (4)y

Magnus Moment*: C" (M, a,p) (.d/2V) (CNPA sina + (5)n

CNPA3 sin 3a 4 CNFA5 sin'a)

Rolling Moment: C t(M,p) = (pd/2V) CLP (6)

*Primes indicate that this is only the Magnius contribution to the side force,

C and the side moment, C.y n"

24

Swhere all tabulated coefficients are functions of Niach nt iber (M)• d is

the reference diameter, and V is the flight velocity.

In addition to the above, the following are also tabulated: the normalforce center of pressure, CPN (in calibers from the nose), the Magnus forcecenter of pressure at 10 and 50 angle of attack, CPF [11 and CPF [5] (fromthe nose) and the secant slope of the Magnus moment (per radian) at 5'angle of attack, CNPA [5]. Note that the designation, dimensions, andphysical properties of the projectiles are included in the description abovethe coefficient tables.

The SPIN73 generated coefficients have not been checked for a tra-jectory match with firing tables, where available, because of the lack oftime; therefore, they have not been perturbed to produce such a match.Based on past experience and the degree of coefficient match reported inReference 22, it is expected that the mismatch is not severe fnr projectileconfigurations within the rar.ge of the data base.

The XM712 (CLGP) coeticients are presented in whatever form thatthey were available in the references. Usually derivatives with respectto angle of attack given in this daza will be Der radiar1 ,ather than in termsof sin a. The Advanced Dev-iopment (AD) configuration had only a fold-ing deflectable crLicifOrn tail and is reported in Reference 23. The Engi-neering Developmcnt configuration added a cruciform set of fixed (indeflection) folding wings and this is reported in Reference 24. Editedexcerpts taken from these soturces are presented in Appendixes C--1 and C-2.

Trajectories and Firing Tables

Complete computer simulated trajectories based on the aerodynamiccoefficients in App indix D and the inertial properties discussed earlierare not available. At the time the termination of this task due to reprogram-m.ing of funds became known, it was decided that a thorough job of generat-ing aerodynamic coefficients and collecting inertial properties on the pro-jectiles was necessary, since it would be impossible to compute trajectoriesat a later date without this data.

Substantial trajectory data are available in this report. The compactedfiring tables of Appendix A have range, deflection (angular), and quadrantelevation information. Most of this is from firing tables (Ref 3-17) whilesome is from computer simulated trajectories available for projectiles ir.development under other projects or from a limited number of firings. It

25

is not claimed that this data can be exactly duplicated using the aerodynamic,inertial, and initial conditions data in this report. Based on past experience

with SPIN73 aerodynamic coefficients, the results should be in fairly goodagreement. Not only is it possible to refer to References 3 to 17 for finer

detail in range than is in the compacted tables of Appendix A but thesereferences contain other information that is not in the compacted tables.Probably the most useful of this additional information is time of flight,angle of fall, terminal velocity, and graphs of altitude versus range. How-

ever, this data is only available for projectiles which have final or pro-visional firing tanles.

The range data on the XM712 CLGP available in Reference 24 isincluded in the Fly Under-Fly Out (FUFO) capability (Fig 8-15). This ispurely analytical data. More information is available in the Addendumunder zoning.

Similar compacted firing tables for those Soviet she-il for which fulltables are available have been generated and are in the Addendum to thisreport.

Control Aeroballistics

The subject of this section is the experimental and analytical investi-

gation of the aerodynamics of projectiles guided by aerodynamic surfaces.The primary method of presenting the information will be bibliographiesof experimental and analytical methods. There is, of course, some overlap.Analytical reports will usually contain experimental comparisons and ex-perimental reports will often discuss and comoare various theories withthe data.

There has been -ome aerodynamic coefficient data on the XM712Cannon Laun.ched CuddPr- c i. colUected and presented it-, Appendixes.C-I (AD) and C-2 (ED) . They represent both its AD (tail alone) and itsED (tail and win.9s) configurations and were taken from Control Aerody-namics Experimental Bibliography items CEI and CE7. Data on a canardcontrolled-fixed tail CLGP design that was not selectecd for EngineeringDevelopment is available in Experimental Bibliography items CE14, CE15,and CE19.

The bibliographies are not meant to be exhaustive or deal with basicaerodynamics. Hopefully the most recent and/or applicable work on aero-dynamic controlled and guided projectiles have been included. It should

2 6 4k

................I

:-)e noted that many of the items listed are titles obtained from a computersearch and have not yet been obtained for a more complete study of theirapplicability.

The analytical methods that could be studied exhibit some areas ofpoor- agreement with experimental results. They also usually do not allowfor more than two surfaces at a particular body station. Multiple surfacecapability is needed for all foreseeable 3rtillery rounds. A typical difficultywith the vortex shedding approach, so widely used, is that for in-line sur-faces (e.g., wing-tail, canard-tail or canard-wing) the vortex shed by theforward surface may be predicted to pass above (under) the rearward sur-face while experiment shows it passes under (above) the surface (seediscussion in CA10) . Other experimental results indicate difficulty in prc-

dicting cross-coupling and roll (spin) effects in general and also staticstability in the transonic velocity flight regime.

As part of another task, preliminary and final aero data packageexperimental programs were suggested for the two configurations proposedfor the CLGP ED program. These experimental efforts were intended toinvestigate the expected trouble areas in both cases without incurring

excessive program costs; a research program would be more extensive.as'.. These programs are attached as Appendixes D-1 and D-2. Appendix D-1

applies to a canard-controlled fixed-tail configuration and Appendix D-2applies to a fixed-wing tail-controlled configuration.

Analytical studies should be pursued to improve techniques espe-cially for in-line surfaces, transonic flight, multiple surfaces; and pitch,yaw, and roll coupling.

Terminal Ballistics

Lethality and Vulnerability

The lethality and vulnerability aspects of terminal ballistics was in-tended to be dealt with by a selected bibliography from the basic source,Reference 25. The fact thit the selection must be based upon the descrip-tions in Reference 25 rather than upon actual study of the possible selections

is unfortur.ate.

The descriptions in Reference 25 are sufficiently clear so that thebibliography for this section includes the most useful material currentlyavailable. Vulnerability of target systems has been included as an aspectof lethality.

9 27

Sensitivity Coefficients

Sensitikity coefficients are, in general, first partial derivatives.

For example, holding all other variables constant, the effect of projectile

weight on range is linearized as AR = (ý- ) a W, where Ris the sensitivity

coefficient for range with respect to weight.

The practice of the US Army is to include such corrections in their

firing tables for muzzle velocity, cross wind, range wind, air temperature,

air density, and projectile weight. Propellant temperature corrections are

also made indirectly. There is usually a separate table which gives the

change in muzzle velocity for a given propellant temperature; this is then

used as a muzzle velocity correction to range.

The only listed correction which is not a true partial derivative is

the one for projectile weight. This range correction includes both the

effect of changed muzzle velocity and the effect of changed ballistic co-

efficient, (W/CxA), during flighi. This is why a separate correction for

muzzle velocity should not be made for a weight variation. The muzzle

velocity correction is to be used for properlant temperature corrections,

as mentioned, and for other effects, such as bore wear.

Firing table corrections may appear to be backwards but this is not

so. An increase in muzzle velocity will, for example, increase range; that

is, !-- > 0. But when one looks at a firing table it will be seen that ior a

muzzle velocity increase (usually tabulated for 1 m/s) the range correctionis given as a negative number, a decrease. This is because the tabulated

range change is to be algebraicahly added to the range desired, producingin this case a shorter range. This will require that the guin elevation be

set so as to produce this shorter range. Then, when the shell really flies

further because of the increase in muzzle velocity, the desired range willbe reached. Similar reasoning applies to all the other corrections and isthe only real difference between corrections and sensitivity coefficients.

(A tail rainge wind is considered an increase and azimuth corrections for

a cross wind are made into the wind.)

Most US Army firing tables give ranges and range corrections in

meters and elevations and azimuths and their corrections in mils. OneArmy mil is defined as 1/6400 of a circle. The usual increments in theindependent variables used are: cross and range winds. 1 knot, muzzle

velocity: I m/s, air temperature: 1%of standard (518.7"R, 288.159K), air

28

density: 1% of standard (0. 002378 slug/ft3 , 1.2250 kg/rm), and projectileweight: usually 1 square (SQ) from a stated standard, e.g., 2 SQ STD.Atomic rounds are marked with their actual numerical weight so their fir-ing table corrections are given per pound.

A further explanation of weight squares follows. Artillery projectilesare stamped with square-shaped marks to give an indication of how faraway the loaded projectile is from some reference weight. The value of asquare is different in terms of pounds from one projectile to another. Theapproximate values for some projectiles are listed below (Table 15) so that

a conversion can be made between squares and pounds. Another point tobe kept in mind is that a particular firing table may use a non-zero numberof squares as the reference weight of a projectile (the one for which thebasic table has been constructed) . This is always given but note must betaken. For example: a projectile is stamped with 4 squares but the standardnumber of squares is given as 2. Therefore, the range correction to be madeis that for + 2 squares not that for + 4 squares.

The compacted firing tables presented for US projectiles in AppendixA contain all the corrections mentioned above where they are dvliiab!ie.The data on those projectiles which have official firing tables or' provisionalfiring tables are usually complete. Whatever data was available from otherprojects has been incorporated into Appendix A. Most of the data, especiallyon projectiles in development, is based on computer simulations but a limitedamount of firing data is also available and has been included. Appendix Ais no exception to all the data in this report; whenever a projectile datumhas been extrapolated unduly or assumed the same as some other projectile,that value is inclosed in parentheses.

Similar compacted firinn tahIes for those Soviet projectiles for whichthe information exists are presented in the Addendum to this report.

9 29

I

Table 15

Approximate relationship between squares and weight

Projectile Standard squares Pounds/square Source 1M329A1 2 0.25 Ref 3

M328A1 2 (= 7 of M329A1) 0.30 Ref 3

M1 2 0.6 Ref 5

M60, Gas 2 0.6 Ref 5

M60, WP 5 1.0 Ref 5

M548 2 0.5 Ref 6

M107 4 1.1 Ref 8

Milo, Gas 4 1.1 Ref 8

Milo, WP 5 1.1 Ref 8

M116 4 1.1 Ref 8

M116, Colored (= 4 of Ml) --- Ref 8

M121, Al 8 1.1 Ref 8

M549 4 1.4 Ref 13

M437A1, A2 3 1.1 Ref 14

MIOG 4 2.5 Ref 15

M404 4 2.5 Ref 17

3@j4

tCONCLUSIONS AND RECOMMENDATIONS

The most up-to-date unclassified aeroballistic data available on USArmy indirect-fire projectiles (105mm and up) has been collected orgenerated. Aeroballistic is used in a very broad sense to include: ex-ternal dimensions, inertial properties, trajectories, zoning, dispersion,sensitivity coefficients, aerodynamic coefficients, lethality and vulner-ability, and controlled projectile aerodynamics.

Classified data in the above areas on US projectiles and all data onSoviet ind Soviet Bloc indirect fire artillery projectiles (100mm and up)which were also collected or generated are in a separate addendum to thismain report.

This study concentrated on generating a complete set of aerodynamicdata without any trajectory information; the rationale being that trajectoriescan be run later with the data. It is not presently known how closer/ thl.eaerodynamic data, when used in simulated trajectories, will match firingtable results. Past experience lends credence to the belief that the matchwill be acceptable.

It is recommended that further work in this area should assure con-sistency between predicted aerodynamic coefficients and firing table resultsand include free-fl ight rocket aeroball istics.

S31

REFERENCES

1. Reichard, B. L. and Downs, A. R., A Compendium of Field Artillery

Facts, BRL Report No. 1759, USA Ballistic Research Laboratories,

February 1975

2.. Reichard, B. L. and Downs, A. R., A Compendium of Classified

Field Artillery Facts (U), ,RL Report No. 1760, USA Ballistic

Research Laboratories, February 1975, Secret

3. Firing Tables, Mortar 4. 2-Inch: M30 Firing Cartridge, H. E.,M329A 1 . . ., Headquarters, Department of the Army, FT 4.2-H-2,

August 1968

4. Firing Tables, Mortar 4.2-Inch, M30, Firing Cartridge, H.E.,

M329A IEI . . ., Headquarters, Department of the Army, FT 4.2-K-I,

August 1974

5. Firing Tables, Cannon, 705mm Howitzer: M2A2 and M2A 7 onHowitzer; Light, Towed: 795mm MA701A I and M101 .1.. FiringC artridge, H. E., M- ...I Headquarters, Department of the Army,FT 105-H-7, May 1971

6. Firing Tables, Cannon, 16,mm Howitzer MA 03, on Howitzer, Light,Seif-Propelled, 705mm, M108 and Cannon, 105mm M137A 1 andM137 on Howitzer, Light, Towed, 105mm, M102 Firing Cartridge,H.E., RA, M5118, Ballistic Research Laboratories, Ft 105-AU-i,October 1974

7. Firing Table Addendum to FT 105-H-6 for Cartridge, H. E., M444,

Headquarters, Department of the Army, FT 105 ADD-B-I, C-4,January 1968

8. Firing Tables, Cannon, 155mm Howitzer, M126 and M126E1 on

Howitzer, Medium, Self-Propelled, 155mm, M109 Firing Projectile,H.E., M107, Headquarters, Department of the Army, FT 155-AH-3,August 1974

9. Firing Tables, Cannon, 7 55mm Howitzer, M785 on Howitzer, MediumSelf-Propelled, 155mm MIO9A 1 . . . Firing Projectile, H.E., Al107,Headquarters, Department of the Army, FT 155-AM-I, September1972

32

10. Firing Tables, Cannon, 155mm Howitzer, M 726E 1 and M 126 anHowitzer, Medium, Self-Propelled: 1 55mm, M 109 Firing Projectile,Atomic, XM454, Headquarters, Department of the Army, FT 1 55-AJ -2,May 1969

11. Firing Tables Addendum to FT 155-A H-2 for Projectife, H. E. M339A 1(M449E2), Headquarters, Department of the Army, FT 1 55-ADD-B-11,November 1967

12. Firing Table Addendum to FT 155-Q-3 for Projectile, H. F., M4'49,Headquarters Department of the At-my, FT 155 ADD-A-i, C-5,January 1968

13. Provisional Firing Tables, Cannon, 1 55mm Howitzer, M126E1 andM1726 on Howitzer, Medium, Self-Propelled 155mm, M 109 FiringProjectile, H.F., RA, M549, Ballistic Research Laboratories, October1974

14". firin /fyl"Tobie, C.ulu,,u,, 175mrm Gun, miii, mi f3E,- on G.un, F-ieldArtillery, Self-Propelled: 1 75mm, M 107 Firing Projectile, H4. E.,,M'i37A 2, M437A 1, Headquarters, Department of the Army, January1970

15. Firing Tables, Cannon, 8-Inch7 Howitzer: . .. 2A 7Il on Howitzer,Heavy, Self-Propelled: 8-Inch, M7 10 Firing Pro jcc~iI., H. E., M 106,Headquarters, Department of the Army, FT 8-J-4~, June 1967

16. Firing Tables, Cannon, 8-Inch Howitzer . . . P42A 1E I on Howitz-er,Heavy, Self-Propelled: 8-Inch. A4 11 Firmna Pro 'iectilp.ý HFS, M424Projectile, A tomic, M422, Headquarters, Dtcpartmeni. of the Ar.-y,FT 80-4, June 1967

17. Firing Table Addendum to FTO-.1-4 for Projeci,lIe. H. E., M404,Headquarters, Department of the Armry, FTI 8 ADi)-A-11, November1967

.8. Hitchcock, H.P., Aerod 'ynamic Data for Spinning Projcctiles,Ballistic Research Laboratories, Report No. 620. October 19147

19. Artillery Ammun~ition: Gtins, How~itzer, Mortars and RecaoillessRifles, Headquarters, EDepartmfnt of the Army, TM 9-1300-203,April 1967

20. Horley, G. and Giordano, D., HELBA T I (Human EnqineeringLaboratory Battalion Artillery Test), LJSAHEL TM-24-70, September1970

21. Indirect Fire Accuracy (U), 3 Vol., JMEM 61S1-3-6-23, 28 June 1974,Confidential

22. Whyte, R. H., SPIN-.73, An Updated Version of the Spinner ComputerProgram, Picatinny Arsenal TR 4588, November 1973

23. Addendum to Cannon Launched Guided Projectile Advanced Develop-ment Program - Final Report (U), Martin Marietta Corp., OrlandoDivision, OR 13, 759-Addendum 1, September 1975, Confidential

24. CLGP (XM712) Cannon Launched Guided Projectile (U), MartinMarietta Corp., Orlando Division, OR 13, 651P, Vol. I1: Technical,14 April 1975, Confidential

25. Index, Specialized Technical Handbooks for Joint Munitions Effective-ie~s Munuais (JMEM) and Reiatcd Pubiicatlons, US Army Materiel

Command, AMCRD-TE, TH 61-1-2, 18June 1975

314

BIBLIOGRAPHIES •-

1. Control Aerodynamics Analytical Bibliography

CAT. The Aero~dynamic Analysis of the Coning Motion of the CLGP, MartiniMarietta Corp. ,Orlando Uivision, Doc. No. ANA 0o900000-002, 13 .€July 1973.

•

CA2. A ecrody-ýnamic Effect o/ CLGP Fin 5we,•,p-buck A ng~le Variotion, MartinMarietta2, Orlando Division, Doc No. AN.IA '107000600.-01G, 6 July 1972

II

UA3. Aero.i•tnornic Methodology. Bodies with Tails a7t Arbitrar'y PollAngle, Fidler, J. F. , Mar'tin Marietta, Orlando Division, O)R 13,375--1,, .Decem b.er 1974 flprepared for A'rmy Missile Co rerml-]rid AD/A-003 3141) :

C,-oi. A Afet-ý-:;d fo," Calc:ulating tha• / erodynemic Loadin(, o17 W•imn- Body, -

dComb .'nct ons at Soall A .ngle_," of A ttock in Sup(:rsonic r- o ti, Jar'kson,C. M. o,,ld Sawyer, W. C-., NASA TN D-6441, Otctober 1971 .

I

CA5. A tlAet rodfnaics : c CAaiytrteiisalBc.ibogrp5d " , Acd Noncirculor Cross Section Alonr andarw'h iettaiCr-p., Orlando a iin'We, oDoAttac, from 0A No 90000C,002, 1L H., NASA TN D-7228, April 1973

CA6. Aerdnatice/ Predicton of the Rofin/fitch end Rok Y: A w Coupiino oM theCLGt, Missir'n, Di.itin ,a Doctta Corp., Orla(ndo Division. 6uoc. No.

ANA 00900000-003, 10 P~u.-ust 1973

CAT. Roseline IV Final Aerodynlgmics, Mrtin wi rietU. Corpit., rarlanlo

D)ivi•sion, Du~c. No• . -. ,-. ' ,,"•"...0 . - .2 7. Feb "LUary 19YI

CA8. Cannon Launcihed C:.ided 4'rojcctilo -Aeroclyr-utnic 0oý,,.,'ti n D.signStudy, Fid'er, J . E and Mi et. t., Oartind Daiviesia Corp., OrlandoDivision, OR 19 ,/4 Vol p, D-c.:ember MI1s73 (prepnred for Naval

Ordnance Sy"siems Command4)

CA9. Compute.- ,1rograai; for CCalulaiting tt.h -trtyic Long it;dinal Aerodyerioin-cbharacceristics of W"inaA- of Coniin Supctonis, Mrendoen ha 1,

M. R., :A al, NASW. (,R-2474, Nielsen Engineering ( ,esearct '7nc.,Januar SAT 1A75

D n.. 35

CAIO. Effoct of Syn1me7trical Vortc',c Sheddirq: on the Iorigiid'ioal Aoro-dynamrtic Char~cterist.:c of Winq -Body-Toil (':),nhifio!icn,Me.-dcenhzall, M. R. and Nicken, J. N NASA CR-214., NielsonCn~gineet Oig f &Reýearc'., Inc., .Janu4ry :V'5

CAII t-ffacts w& thi For wcard Sirakes on CLGP Coning Motion, MartinNlar~ezta Corp , Ori-1ndo Division, r~oc, No. /-,NA GOOO0O-OWJ.,13 August i~ii3

CUl12. Estimoaicd Aet ociynonic C (jur~ac &iýr.'stics 1-or tWe Bc,Sc.JinV C1.6"' Coll-ficui-A~ion, Martin kim ictia Corp., Orlanc-lo Division, Do~c, No.ANA 10700000 00t, 3 April 1972

CAI 3. Estimated Aer-odyna-mic Charactcris tics for iNinc C'!GP Configo-~rations~, Mar~tin MA~,etta O-lancio Division, Doc. No. A.'A107000~00-02, 13, Apr#i 1912

CAI 4. Estimated Aoroclynomics for the Baseline bli CL(,P confiLjo. i"olion,Martin Mairietta, Or-lando Division, Doc. No. LNA 1IO;'COO0U-O'J7,8 May 1972

C-A I . Estiniatmont c,7 ih -,,. ro- lift Drag cf Missile :n'fj, urct;,lns in 5up'.---son;(c. F,'ovn vlth 7.i.'buleni onurdary, Lvop-r. Ja~ksoo, C. M., 6al, NAS.A TfM >(890, 1 969

CAI 6. L I if,' in jC>,jr ter (of FP"e. ':urtc. of i' u W(-FSu1.y'-r 0 ai1 (ii~~io tScthsop~ic. 7.i-onsonic, cir-d Stpcrsoolc Spl-eds, Pivs, W. Cet :%I. JAC\ upoit No. 1-1,07, I 957

(cA 17. Me,.lod f'Colcuiritincq ind'. (ýd . %Vimii Mon. -Žrj(s for C'-ucifo,':,Cji;4 ~s~ile s Angles of A,'Lack u!" to 20 Ot.c', Pic'nSch, M. J.

cL 0i!, IeNIv4*e (, -.ts'.rs, ,.... I 5761,',A M Iy 1 7

CAI 8. Alumericd MUUocjs fovr- the !)csiz~n cml Ancl's.-- (-f IWincs ' Super-Sonir S~,es Ca;-, 3on, 1. VV- 2% Miler-, D. 5 . NAIS. ý IN o-7713", Dececnhcý: 1974

CE1. Adcdeml irn to Careiuor Launched Gui~dcl Projcct. '- A.w.yv.ýce.0i~hEop',e 11Progyrcm - Ci~lReport, (U) . '.actiri LY,? iiata Corp.

Orlcondo Pivisioo, OR 13,759 - Addcr~duni 1, S5epteimber 1,j!5,Coofidentied

I

I

CE2. Aerodynamic Characteristics of a Canard-Control Modular WeaponClussification at Transonic Mach Numbers, Kaupp, H., Jr., ArnoldEngineering Development Center, AAEDC-TR-73-134, for Air Force

Armaments Laboratory, August 1973

C.E3. An Experimental Investigation of the A erodynamic Characteristicsof Several Nose-Mounted Canard Configurations at Supersonic Mach

Number, Burt, J. R., Jr., US Army Missile Command Tech ReportP-D-75-17, 30 Jinuary 1975

CE'l. An Experimental Investigation of the Aerodynamic Characteristics

of Several Nose-Mounted Canard Configurations at Transonic MachNumbers, Burt, J. R., Jr., US Army Missile Command, TechReport P-D-75-2, 30 August 19174

CES. Best Estirrited Values of CL Trim and 8 Trim Based on Wind

Tunnel Data, Martin Marietta Corp., Orlando Division, Doc. No.

ANA 00900000-005, 15 August 1973

CE6. Canard Control Effectiveness Study on the Air Force Addvanced?actical Rocket at Mach Numbers 2, 3, 4, and 5, StriKe, W. T.,Jr., Arnold Engin,•ering Development Center, AEDC-CR-74-34,

for Air Force A.-marnents Laboratory, April 197'4

CE7. Cannon Launched Guided Projectile (U), Martin Marictta Corp.,Orlando Division, OR 13,651P, Vol. II: Technical, 14April 1975,Confidential

CE8. CLGP Wind Tunnel Test Plans and Po-st-Test Report, MartinMarietta Corp., Orlando Division, Doc. No. ANA 10700000-008,16 June 1972

CE9. Effect of Several Canard Sizes on the Static Stability, Performance,and r-rim Characteris tics of the PAVESTORM I Munition System atTransonic Speeds, Smith, D. K , Arnold Engineering Development

Center, AEDC--TR-72-67, for Air Force Armaments Laboratory,

Mey 1972

CE 10. Effects of Nose Bluntness on Aerodynamic Characteristics ofCruciform - Finned Missile Configursition at Mach 1. 50 to 2.86,JerrnelI, L. S, N.ASA I M X-2031, June 1970

37

kI

GEl 1. Lffect of Wing Plarnform and Canard Location and Georretry on theLongitudinal Aerodynamic Characteristics of a Close -C oupl.odCanard-Wing Mlodel at Subsonic Speeds, Gloss, B. B,, NASA TND-7910, June 1975

CE 12. Elimination of the Induced Roll of a Canard Control Con figur-ationby Use of a Freely Spinning Tail (U), Darl ington, J. A., NavalIOrdnance Laboratory, NOLTR-72- 197, August 1972, Confidential

CE1 3. Preliminary Static and MAlgnus Measurements on a Proposca Canard-Controlled Guided Projectile, Regan, F. J , Naval OrdnanceLaboratory Wind Tunnel Report No. 80, April 1974

GEl 4. Static Force Te.Ft on a 0. 7 Scale Cannon Launched Guided Pro 'ifcctileat the VA C High Speed Wind 7 unnel in the Mach Range of 0. r, to 2. 5.Box, D. M., Vought Systems Division Report No. HSWT Test 438

(for Texas Instruments, Inc.), June 1972

CEl 5. Static Force Test on a 0. 7 Scale Cannon Launched Guided Pro jec~ileu.J " I fIU Vi/, k.iiyi 17119 L WV>ee Iri IU Tui-i- U iii i htf IlVfUCI Rur'IyL ul' 0. 6 Iu. 21.5

Second Series, Box, D. M'., Vought Systems Division Report No.

HSWT Test 4146 (for Texas Instruments, Inc.) , 19 Septem~ber 1972

GElS5. Static Stability and Canard Hinge-Moment Characteristics of theAIM-9J (Side Winder) Missile at Mach Alumbers from 0. 4 to 3. 4 (U),Arnold Engineering Development Center, AEU-%C-TR-72-34, FinalReport 11 October - 12 November 1971

CE1 7. Supersonic lnthrference Effects in Low-A spect-Rutia Planer Con-figurations at Large Angles of Attack. Hart, H. H. , Applied PhysicsLaboratory, Johiis Hopkins University, TG-998, July 1968

GEl 8. VSD High Spe-ed Wind Tunnel Force Test on a 0. 70 Scale 7 55mmCannon Launched Guided Projectile in the Mach Number' Range of0. 6 to 2.2, Popce, T. C., Voight Systems Division Report No. HSWTTest 487 (for Texas Instr uments, Inc.), 25 March 19714

3. Lethality and Vulneraý)ility Bibliography

(Index: Speci~ilized Technical Handbooks for Joint Munitions EffectivenessManuals (JMEN) , TH 61-1-2, 18 June 1975)

LV1. 61A1-3-1 Target Vulnerab;Ility (U), Secret, 13 Feb 74.

36

LV2. 61JTCG/ME-69.-1 Target Vulnerability Scaling and Modeling,31 Jan 74

LV3. 61JTCG/ME-69-2 Target Vulnerability Symposium (U), Secret,15 Apr 69

LV4. 61JTCG/ME-69-3-2 Lethality of US Ammunition Against SovietArmored Vehicles (U), Secret, 1 Jan 70

LV5. 61JCTG/ME-69-3-10 Blast Effects on Soviet Vehicles (U), Secret,12 Mar 71

LV6. 61JTCG/ME-69-3-11 Vulnerability of Selected Soviet HE Projectilesto Fragment Impact (U), Confidential, 14 Aug 71

LV7. 61JTCG/ME-70-6-1 JMEM Computer Program for General Full Spray

Personnel Mean Area of Effectiveness Computa-

tions (IJ) , Confidential, 25 May 71

LV8. 61JTCG/ME-70-6-2 JMEM Computer Program for General Full SprayPersonnel Mean Area of Effectiveness Computa-tions (U), Secret

LV9. 61JTCG/ME-73-6 Lethality Prcdictions for US Army MunitionsTested in Various Environments in the DepStatic Arrays (U), Confidential, 25 Apr 73

LV1O. 61JTCG/ME-7;-9 Effectiveness Distribution for US Army ImprovedConventional Munitions, Confidential

LVI1. 61S1-2-2 Effectiveness Data for Howitzer, 105MM M101A1(U), Confidential, 11 Dec 72

LV12. 61S1-2-3 Effectiveness Data for Howitzer, 1355M,4, M109(U), Confidential, 11 Dec 72

LV13. 61S1-2-4 Effectiveness Data for Howitzer, 8-1i.ch Ml10(U), Confidential, 18 Dec 72

LV14. 61S1-2-5 Effectiveness Data for Gun, 175MM M107 (U),Confidential, 18 Dec 72

LV15. 61S1-2-6 Effectiveness Data for Mortar, 4.2 Inch M30(U), Confidential, 15 May 72

LV16. 61S1-2-8 Effectiveness Data for Rocket, 762MM M50 (UL),Confidential, 3, Oct 72

LV17. 61S1-2-13 Effectiveness Data for 155MM Howitzer M109A1(U), Confidential

39

LV18. 61S1-3-2 Safe Distances for Fragmenting Munitions (U),

Confidential, 19 Mar 73

LV19. 61S1-3-3 Lethal Areas of Selected tJS Army, US Navy,and US Marine Corps Surface-to-SurfaceWeapons Against Personnel and Military Targets(U), Confidential

LV20. 61S1-3-4 Manual of Fragmentation Data (U), Confidential

LV21. 61S1-3-5 Ammunition Reliability Report (U), 15 Oct 75

40

-S-do 1 CIIc

d3 II

0CL

f.

41~

120

80

VII (charge)

v10

-• 40

t w

v I

0 2 4 6 10

Range (Km)

80[

40!

Lu VII (ch.rge)

•;0 • !r_ .,-i - r,ýision

0 2 4 6 8 10(FT lOb H.7)

Range (Krn)

Fig 2. MIOlAl (105mm) MPI probable error firing M1 HE projectile

42

t

120

80 V VII (charge)

S• J f J P,'ecision (FT 155-AH-3)V V

0'

04 8 12

• Range (Kml

80r

£F 40

E V1 (carge)

!t- Precision (FT 155 AH-3)

0 8 12

Range (Kin)

Fig 3. M109 (155mm) MPI probable error firing M107 HE projectile

40

120

80 VII (hargelRA VII

"Preci5iorn (FT 155-AL-0)

- - "robatulV IToo high)

".u#

LU 40a-

0 --__ _ _ __ _ __ _ _ I ____

0 4 8 12 20

Range (Kin)

80[

40 VII W(harge)

-- RA

U .1 VIIS• • RA

Tt - . .i Precision

0 4 8 12 16 20 (FTr 1&-AL-0)

Range (Krn)

Fig 4. M109 (155mm) MPI probable error firing M5i9 RA projectile

44

I

VII (Charge)

80 Vw

111w

40- VII

- • * Precision (FT 15,-AM-1)

-a--

0 4 8 12 16

Ranw. (Km)

4

80

Soo

40 - VII (Charge)

LU ViIa. .ui=., Precision (FT 15býAM-I)

0 -

0 4 12 16

Rvign (Kin;

Fig 5. MIM9AI (155mm) MPI probable error firing M137 HE projectile

45

1160

120 VII (Charge~)

4 /V

80/

LIII

40

VI IPrecision (FT-8&J-4)

00 4 8 12 16

AR0iye 1Km,)

40-

01 ___________ - - Precisino (FT 13J 4)

0 4 8 12 li6

Pag (Kin)

Figj 6. M110 (203mm.) MPI probable er, or firing M106 HE pvojp.LtI e

46

.1I 'A

2C/

8 ;1•(charge)

( /1 7.,1

0 4 8 12 "16 20 24 28 30

RHnje (KWi)

120

c

.2 80

I ,' 40 / •f /,

4 11(chu•g)

O-I II-- -_ (-"---4 -175 -A-1)

"0 412 16 20 24 28 30

RA6le Mr.-)

Fia 7. M107 (175mm) ? .PI probable err or firing MU37E2 HE proje ctile

47

74

~Qc

_J 0

z w -

*tLi L--U, 0-

F,- .T- p .

-2(

X 0 oNo 2

Lva x -van .0

N U~N04o

ILI

Iz

-0-4Lc0

U -JIa-__ 0 -

EE

ma_ _ _ -W

70 0 /

0.W W

*z 0

UVA - w -voU 0aa x~ (2nu

I.- aMC U 49

CHANG2 .9 AL1S I t~C L I'

CHARGE Z flE 10U pr. iPýM' te~Ci PY (KM?'

Xjj2C U I 19 244

XM1US AAik'k 26j b110 1662.30 1,i3 126

T 0 3- fTH4 .\%LT "UDE - ~ iS ETy

0M0 T, IMPACT TIMEI

41 CIf'tB LI)'iPAT 71 /'IANA .SF&

t Olt( Z 4R 020

a9 4 a aE0 1 z

OGtFIULD IANGE' k,

F~g 12. FtJF rag 'xtniafu X1BALII hlowCtze

50- Q IEl KA q.A ýP le

Vi '0 2M4A .. *0M109I j C IQ. 3 W4

10

XMIW HOWITZERZONE NO. 7YM21I E2 CHARGE ""Of ý 45 DIOPfiE /

I NOTT 21.2 KILU)METERS IMLE MAXIMU'AEXTTENDN AG SEYND 203• KILOIEERS

I CQUISITION COND!TIOkS. (0.6 TARGET

REFLECTANCE 116MJ LAER

2I

4 7"3 -

22

NOINALIFUFOAN4E IRN

19 20 204 2022 21.

FLVOUl RANGE KM

Fig 13. Maximum FUF'O 9uided range, XM198 howitzer

5.

BALLISTIC IMPACT

at (OEfAl IMPACT POINT (KIM) TIME (SEC)

75 4 ,'4 49

70 L, 14 4 : 10M109A1 5 679 4I.0

30 5 02 k7 3

15 30 146

12

-- ~ 7 30 DEQR10

11 U5D DEGRE

90 2 GA f

Fig 14i. ,Minimum ran~ge trajectories with MI09A1 howitzer, charge 4

52

BALLISI Kji~-ZI SE (DEGI UI4PAcTr POmIFhl() iIM ~im.E:sfC)

70 364 7

8 6 476 4b 330 40216 3.10 1 3.6

it.4AIj 10.310 -

78 DJEGREE 1

ii~6 25 EofttI.

is 5 iiu ag taetrc ihX19 oizr hre'

F J.)

4I1 30 ~gn-

I I I#7 46,lw I ,

U. 1.0

.u

I.#4 700 NO 460

f 1#4 65, -#6 46c#4 C,00 -#4 450

o / .LSI =- I00FE CIU

2. 4 "- 4i-

MN. NRANGE T KM MAX. FLY OUT

Fig 16. Trajctory flexibility due to FJFO and hig/iti ow OF options

>.1.0 - - - - -- _ _

rt

0 OALLISTIC 3WFEET CEIUI'eGL .6

0O.4IC OBAL(LISTIC = FAýIR WEATHER

_____ FUFO =i 300FEET CF. ING/

I FUFO = FAI$ WEATHER

o 4 G 16 20 4TARGET RANGE -- KM

F 17. Engagement probabili, ballistic and FUFO

i54

APPENDIX A

COMPACTED FIRING TABLES OR SIMULATIONS

4, 55

.. '.

.,..• - ),_ - ° . , , . ;.r-• - _ .. ,~ ,• •.,

5�

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I .. I � I II IA I C C C I CO 0 0 0 -� -'

a" � a' 5 . I II I II..'. I - - - -I I II +

I C 5, 0 0' Csit I 0 0

0. 45.' C '- I.

K 0 .C II .�

' I V �1 t� oh :ITtI7171 1I !211j..

C 4 a.

C -, 0 0 - 0j 0 a- 0 -

00 000]

5, 00 -� '�a £

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APPENDIX B

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,ARPENDIX C

CANNON-LAUNCHED GUIDED PROJECTILE AERODYNAMIC DATA

XM712 AD configuratier,

T 9

- - - - - -- - - - - - - - - -~

This summarizes the pertinent data rnrd conclusions pertaining to the

aerodynamic characteristics and flight test performance of the Cannon

Launched Cuided Projectile (CLGP) configuration. The de'velopment of th-

aerodynamic characterization of this c-,figuration is briefly surrmarized,

including both theoretical analyses and wind tunnel and fiight test results.

A combination of theoretical anal' :3,e-, v"ind tunnel testing and flight

testing was utiiized to examine the aerodynamic performance capabilities

of the CLGP airframe. The aerodynamic properties )f the first basic CLGP

configuration were obtained by utilizing tile Martin-developed "CAMS com-

puter program. The CAMS (Computer Aided Missile Synthesis) program

aerodynamic module is basically a computerized adaptation and extension

of the US Ai- Force DATCOM Stability and Control Handbook. The CAMSprogram contains provisions to evaluate both finear and nonlinear con-

tributions to aerodynamic coefficients, including the influence c.n alt lifting

surfaces of vortices gEnerated by forward lifting surfaces, body vortex

effects on !ifting surfaces, aid stall characteristics. Initial CL.GP aero-

dynamics were based on a configuration with a length of 47 inches, .;'r-respur,ding to the alter nate proposed configuration.

In order to verify the aerodynamic characterisijis as predicted by

the CAMS pro-ram, a wind tunnel tes-t ,.as also- cond,_,tcd during the

proposal preparation. A 75 percent szale model was constructed of alumi-

num with high strength steel fins was used. This model included bour-

reaets and the rear-mounted cbturator. TIe test were conducted in the

Ling-.rernco \.!oujhL 4,-fout, high speed wind tunnel facility through a Mach

nurnbhr range of 0.4 to 2.2, with Reynold's numbers of 6.55x106 to

7.07xl06 per foot. The model was mounted tn a bent sting that had an

angle-of-attack range of from --5 to +3) degrees. The tail fins were man-

uaily adjustable with settings at 5-degr-. irncremerts from -2r tc +10

deqreeý. Data from the wind tunnel test in general substantiated the pre-

dicted aerodynamic characteristics as developed by the CAMS program,with the 'llowing exceptiors. To obtain equivalent trim values of normal

force coefficient, the test indicated a required increase in angle of attack

of 2 to 3 degrees and approximately a 5-degree increase in fin deflcction.

Extaction of linear values of normal force, pitching moment and control

power from test data at subsonic Mach numbers revealed a reduction frompredicted values of 30 to 35 percert. Following the wind tunnel test, aero-d'namic coefficient revisions were inc-orporated :n the 6--degree -of-Ireedom

system simulation program in order to bring the aerodynamic data inputs

into agreement with the wind tunne! results.

221

BOecause the wind tunnel test was conducted on a 75 percent scalemodel of the 47-inch proposed alternate baseline configuration, it wasnecessary to apply corrections in order to characterize the 54-inch air-frame. These corrections were based upon theoretical modificati,,ns tothe 47-inch wind tunnel data.

The addition of four strakes to the optical nose corne of the BaselineCLGP produced a new configuration identified as Baseline Ill. Estimatedaerodynamic characteristics of this configuration were outained by appl\'-ing theoretical corrections to the baseline aerodynamics in order to ac-coun. for the four large strakes on the nose.

At the time the Baseiine III aerodynamic char3cteristics were de-veloped, it was recogni7ed that another wind tunnel test would be requiredin order to verify the predicted coefficients. A series of tests was conductedin May 1972 at both the Ling-Temco-Vought High Speed Wind Tunnel andthe Arnold Engineering Development Center Propulsion Wind Tunnel (4T).In general, substantiation of earlier data was obtained, with the exceptionthat the Baseli.--e II! configuration with lat ge-size strakes was found, duringthe LTV test, to be statically unstable at the higher Mach numbers. There-fore, emphasis during the AEDC test was placed en a configuration with avery much redLCed strake area which was sUbsequently to develop intothe curt ent Baseline IV configuration. The aerodynamic characteristicsof thc Baseline IV airframe are given. These data represent the currentaerodynamic characterization of the CLGP configuration.

Tht following four pIcts (Figures 2 through 5) present out-of-planeaerodynamic coefficients on a body axis system for roll attitudes of G, 22.5,45, and 90 degreeas. They were derived from the AEDC wind tunnel testdata, •:nd are based on 5 degrees of rolil ccmmand.They are directly applic-able to the nitching and yawing moments deriving from vertical fin (num-bers 1 and 3) roll deflections. The similar contributions of the horizontalfins (numbces 2 and 4) may; be obta-ned from the four plots as foilows:

Use 4=0' for { 90'

* 22.50 for * 112.50

- =450 for * 1350

*=90' for 0 0'

and switch C and CMY

u and p

222

where C MPis the pitching moment coefficient

C MYis the y-aving moment coefficient

a is the pitchi angle of &ttack

0 is the yavv angie of attlack

.'ith the addition of these out-of-plane coefficieýnts to the aerodynamics,the test flight coning behavior was then predicted,

Fxamiriation of fl'ght test reiuits aist; pr-irtted out a discrepancyI betweýen predicted and 'actual roll rates during ballistic flight. Roil rateswere typically' 10 to 20 percent lower 'han pre(Bc-tedl. Roli power was sub-sequently redefirnod aý3 a function of total f;io incident ar~gie rather than theprevious fin deflection alone. Fin~ incidcit. angle is dlefined as the sum offree-stream or bodv. ang~le of attack, fir, oeflectior1 , and body upwash. Inthe lateral case, it is the sum Jbody sicde-,lip angle, fin -deflec-tion, aridbody sideviash. $;i~ce the CLGP_ 15 t5)rFi1HeLr ci~a dbot~ its X-A axi5, arikle,of attack and body upwash are interchangeable with sideslip angie anI body sidewash.

To evaluate body upwash (and sidewash) , plots of angle of attackversus pitching moment coefficient were drawni for the body along and for,

the body plus fins at seve/.ral fin deflections. At the angle of attaeck forwhich the body and the body plus deflected fin pitch moment coefficientsare equal , the fin incident angle must be zero. Knowing the drigle ofattack arid fin deflection for each intersection then provides a solutiorn for

body upwash as a function oi angle of ati~ack and thus the slope of upwash

with angle of attack. Thns2: solutions were repeated for each of the windtunnel data Mach numbers to provide the upwash slope variation with Machnumber.

With the f in incident angl e thus lef in ýd, rollI power wa-, then gen-erated from the wind tunnel data as a function of this angle for severalMach numbw-,-. These data are shown on Figure 6. Note that total rollingmoment coefficient is then dlefioed as:

223

Cg - &•M, 81 1( I do

d._" C M, 82 - 1 +da'

"+ C &A, 8 3 +13 1 +d--aQC dp, -

"+ C M, 64 +a 1 +d- IThis inclusion of upward (or sidewash) in the aerodynamics then

provided a close match with test roll rates.

In summary, the aerodynamics as presented in this report are con-sidered adequate io descr be the AD CLGP flight environment as verifiedby comparison w;th test flights. The major conclusion to be drawn fromthis report is th3t, based up-n existing flight test data and analyse,., theBaeline IV Final Aerodynamics appear to adequately describe the C.LGPairframe aerod,/naric characteri st;cs.

The inci'Jded curves of aerodynamic coefficients are those datarecommended for use in flight simulations of the CLGP projectile. Stabilityand control, axial ,orce, roll characteristics, and damping derivativeshave been given for projectile roll attitudes of 0 and 45 degrees.

The data curves given were based on wind tunnel data measured ona 75 perceni scale modae tested during May 1972, Figure 7 presents theaxis system and sign convention, Reference area and length for all co--efficierts were 0.196 ft 2 arid 0.5 ft, re.spectively. The collected aerodynamiccoefficients are plotted in Figures 8-34.

224

9!

Figure 1 in the report from which this Appendix C is excerpted

was rnot needed.

tI

225

1.

S. . . .. ... - - .

•'.:,1 " ' . I. • : r : •

SI ' 1 ' . ,CLL

U, .W A W; iA i . .A. ..

So , •- . .i . :. • ....... . ..C. 0:

c~oI ,, ' I~

- . -.

• I . . . .I •

L.. . .

Fig 2. Pitching moment and yawing moment due to roll command

226

I I I I l I • I I l I I • l II

/JII

.17

vO&,, ; " ;I .

0.04

"0- 1* +

o a . .. . ... .- I , --QIi i .• *i " . .N' i-.' tO

.I.flI'.< -- Q--.r -" . -...

I' ' • , f . . 4 -SO,+O'• .... .... ...... ......... ". .p.1.:+.:• [

0.014 -

,L,,

,0 -+--0.... -1.

.A7cx.+o ,w.~.- , .1- . . .

F;9 3. Pitching moment and yawing moment due to roll command

227

..- ,tg..t, *. 44.+ n +\

' ; ' :

boa-<;NvI

A~M OA

0

0.0.1

0.01 T

0-

LJJ

YL

Uki

./KU. Gci

Fin . Pthn oetadywn mmn u or0 omn

228

0•".

,• o2 4 ti. i . • • - / , .

0Z.

/~l-o o I, I : ,••# .\ I'it

0 4 . '

0. 09 *. . .L . ".:H.T . .1 ts•/:.o. 8

W -0.041.,i

.

0

,. . 'I

"2°S - .o , \o q :. •: . %. ,. I i'•t -! :

S~Fig S. Pitching moment and yawing moment due to r-oll command

229

to .0t,

"4J

IT FOR:, 'M=|•

1*'. ,1

0 jz

AD,

20e

IPJ

0---Fig 6. Roll power

230

.4.

.,,ý I4

<i-9 - I,

TI MEELC.0

Sr-ig -7. Axis system and sign conventhiti

231

s m" 0 0 -S- .I.uV 0 jO 17

C ~ 5 5 0-S

-3r,

0 0 -1 () 5 Ale

S0 -e 33

/1

0

to It. 0o FT

F i . L r- t u i a s t b l t , . 4

'413'

S. . ... . • ... .. ._ _ -1 V

-2 11

Fig 8. L o,. tudina l stabiiity, M O .•, do = 0 0

232

,/ ISYM SJ ,4 , RUN

V 10 -10 57

o 5 5 59

-1 I's 59 . .- . ... .X _.

c~-2-0 20 ss asI~

- __ -- __, ._'I 6•• "'

20'

-.. . . . :- .. .. , ,U -

0*

(,,~~~ ..- o--4G4-

C 4cG a 32.14

Sv, .19(p F T,. ,O.S FT

4

Fig 9. Longitudinal stability,M 0.4, 450

23?

I

o~h " '. f.: -, '.RkIo 0 0 11a -5 0 . 0o -10 0 300

0 -zo o 32 ,-••

o I

P• - .*oF'T

Fig 1'). Longitudinal stahi~iH',-M =0.8, qb=0

234

ft

Sto -10- "2

0 0 0 a

,/-5 5* 4 ..--

(3 -i-0--i 15 7SI 4-19

C-20 0~ 75C~ as,

""2

. Fig 11 Longitudinal stability, 0 z 0.8, 45°

235

6I

S I .,~ S" RUN6

* 0 -10 0 22

0 020 2i.1 0 Is

236

0:

VVi

00

in 0 r

0 0 0 0

237-

'K'0 0

*2 8

I

*1

0C 0 -

-p 1/

CM -~0

-l

dw ' 0..5 f T

Fig15. Longitudinal stability, M = 1.3, 4 = L5'

2P>• ~239 .

S.. . -,i

II

N x

"" L• MIX

,•--.-. . ....... J

.. • . -2Z-•.

Fig 16. Pitching moment dUe to str'ake S., 0

240

- M~r~ts$7D vrs

/ .191

I

-t •. -. -. . . .

LII

I. - A. ... "

e~ • • .f 2.0 t4

Fig 17. Pitching moment due to strake S•, •p = 45'

S2141

II

I

cw.0

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

lOg

I -j

Fig 18. Longitudinal stability .M 1.8

242

. ... * *3

t

0.7

0.3.

-MC N V4%S,.-

"I I

I I

243

0.I

0 0.4. 0.8 L . ,

MACH t•U MeER.

i ~~Fig 19. Axial Force, 0 = 0u & 45° a = 0°5, o 0, altitude = 4000 ft

243

1A

SY(V S 's'" RUN

V 00 - 5 37 164 y

o 0 -0 6 .

4)1C 0 5 (.

CA --~t5 545

oi 0 Axia Forc M3 = ..4 0atiu 00f21C

t

rYM S*,,$ J.,,S RUWI1.4 . . . . . ... .. .. . .. . ...

/ 17 -10 10 57

_0 0 0 &.o - 5

...-. - lo -o 4

5 --6 5

o • , _-o- 5---

C.8'

* . .. '

N N

0 a DEtPXEES

Im Fig 21. Axial Force M 0.4, 4 &lt•itude 4000 ft

24I

/i

7 1 0 0 18

S 0 -0 t

bo

O 2 0; 0 E

._-- t~bEGREE.S

Fig 22 Axis! force M = 0.8, - 0, a4ti., ," 4000 't

2416

t•

IA ..5& F -10 '0 72C D - (. 5

0 0 0 7

" A -,5 (4

0 .01 -10o w7A is -is 74

~ ao-~o75

:!4

.Z

0 5 10

(-" T)ECRECS

Fig 23. Axial force M = 0.8, - 45I, alt-tude 4000 ft

247

C 0 5 20vo 10 15 2" 0 0

CA

_-----F--.. .__

CI2

Ca-

0 20 EOIS•oZ

01- DEGR(-LUS

Fig 21;. Axial force M = . , 1 : 0?, altitude = 4000 ft

248

4

I • ik .i1 T fAI' U

".l&FT•" Y• ,, , k

94V -1o t10 8-

0 ... O o 14

o 1 $4

Ca

oZ

ao 5 IQ VS•oZ

Fig 25. Axial rorce M = 1.0, { =45° altitude 4000 ft

249

/

- I-.. . ..M ' SYM , , RUN" .

13 0 2 1 5 (PAEDC)LS D /_ 0 I 0 o iz • (LTV)__ '..... . . ... .

CA.. . . . . - . ,1 -_

S.......... - ....-- - - - - - - - - - - - - - - -- - - - -- - .....- -- •-- -- - -.. ....

.8 a... ..

01----.d-D- 3GRE•5

Fig 2G. Axial force M 1.3 & 1.8. O 0laititudc- 4000 ft,81 3 = 2 40

250

.;2

M.YI • If ......EDC...............

1.3 a0 Z7 (FEDC_

0 D olo 2 (LTV)

1.0 .. ..-. . . . . . . . . . . . .

.0

CO,

.4

0100 AC I0 I 20 E-s

Fig 27. Axial force M = 1.3 & 1.8, • - 45V altitude 4000 ft.8 t 3 = 62 4 = 0

251

06D4 0

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

402 I,01

0SO -f 0.6 1,2 1. 6,,

Fig 28. Roll power-, C, I =

252

M

VMA H UUM 8EO RG &v

A(

Fig 29. Rol power, C , 5

253

4,0

( LoEr.

IJWQ F fC;CKab.

&Z0

o0

aa 4 10z

LLp

4 8z 16 2

Fig 30. Induced roll coefficientMoc 0.4S

254

/w

1450

I.-o

.0 .f Id. 1

- *O J i)LE0

0.1J90GLE OPq-AL

0~ '4

0. o

z -20

A i1

I-HUXL Uf 9-f TACIK C<ba

5x- z -- --

Fig 3?. If(auce- ru'!C tcl.rIM 1.0

256

I

-300

2!00

°. 4:OO

.- '0 . "- B C..

-300

- 200

MbX -

- I00

Fig 33. Pitch dampirn,, 0O

257

30 Ctrs .... I

10

•F~Ct. lJUMAER

Fig 34. Roll damping, C,, a 00

p

253

11

I

APPENDIX C

CANNON-LAUNCHED GUIDWD PROJECTILE AERODYNAMIC DATA

SXM712 ED coInfigato I

9259

-?" .• ,I.:•. "." 4• .• -. -G •.,:•'•,,a•.:,-W..M '...,• _.,•:I

• I I I I I I I I I I II I I

GEOMETRY AND MASS PROPERTIES

1 hesc are presented in Figure 3$.

AERODYNAMIC PROPERTIES

Static. stability, drag buildup, and control effectiveri:-s dzta wereobtained !- :;rn a 75-percent scale model wind tunnel test conducted i-nMarch 1975. TIh-moretical czlculations were performed to define the dynamricdlamping coefficients. Ti 1-e values calculated wore thien correlated withsimilar data for- the AD -LGk",. with good agreement. No -aerodynarnic cr~isý;coupling and control interaction eifects vv~re measured.

The ae:-cdynarnic: data on Figu-e~s 3G through 49 are presented in abo~dy axis sys'em about a center of grzvity located F. 17 ciJlbers aft of thenose. The refer ence area is 0.1 it6 ft 2 and the reference length is 0. 5 foot.

Pote,ýtial!v, critiv-al cortfiguration areas have been minimized in theproposed conficuration. -The fins were sizeo to provideo a one-hailt caliberstatic margin at t!,e highe5.t 1aunich kloci ~ii-; The vvings wf're th~en

t sized to maximize tr'm loadi factor capability at the low.Aer mach numbersthat will be encount~red in maneuvering flight, and a~t the iame time, becompatible 6.th the ;pn restrictions imposed by the- foldout concept.

Model buildup ý riS were conduc-ted to provide critical evaluationof forebdV.ý, base, firý, arc: wing d;-ag. Trhc effýcfs o, tiurrelets, openslatted coni-roi hou:.ing, ar~d c.:tngravprJ obtui-ator were- evuluated duringA-) tesd no. These c'at; confirm p; ictec: configuration range performance.

Dur-ing AD fliqhi. tý-stdng, configuration inslabilities; arising fromaerodvnarric; crot s (cou,. irng were exoewiricced. Consequo'ntiy these cress.coupling coefficiknr; were estima ted

J4

- ý '-

-c!J 0ý c4e , 4m .;* r c

6v w

0 -0

Fiq 35 eo er ai as rpete

631

,%ODY-WINU-TAIL glau l 0.1il F--

0.4 _ _.

0-t

SODY-TAIL

ý, 0.4 O. 22 •d.0

MACH• NUMBER

KOWAPAL FORCE COiFFiC11"T "•Pt VIERSO8 MACH SU•M6111

Fig 36. Normal f'orce coefficient sJ,..pe versus Mach number

0264

selfl " GIN FT'4a0 - ,j.I- FT

* I-Q4

2 I

CODY .TAIL

II

0 4 0.0 2 Is 2.0

M'CHN UMBER

Fig 37. Pitching rnomený coefficient slope versus Mach number

*11

a< a <a D•,p i Sa darp - U0.1b T

1 _ _

- ~NL.PY-TAI, 1SOL'I'- -1%4-..-0 Te

FMAg N3JM. Ev M

Fig 38. Ct~'er of pressure ver'sus Mach-F'unuber

I'

26 i,

600V WInM TAIL

BODY TAIL in 9-

o I

02

BlASD ON krV TiST DATA601 - 2 PFIN MOLL POK'CTIOMN MARCH 191

MACH HUMIR~dll M

Fig 39. Axia; force coefficient versus Mach rnumber

alo ep - 0.190I _

0 MAUDi ON LTV TRIET DATA BS•II~AR•CH 1il76I

iCI~ 1100Y*v

CLEAN r0.F I0i 10

C.AN" 06OO*0

Fig 40. Axial force coefficient breakdown

"6 266; IAA M D~g I I I I I-a

I II II FIIgI I O AxIal forc cIeIdInI brIdw

COEFFICIENT VCSf.U4 flIO DIELECTIZV

6 MACH 0 %1

*0 14'I W a .6.

04

01,

02 0100 0 -ACH 0-

0 2a-I i.o. -b 20 -i

ersf, in deTfi 0

0 -0. 0

• 'i • I|AC(1-,'.-l O.

03 0.'

0 a -

-01 0-0a 0.

01 -1lb

-o

,10 10 -10 -20 -30 J

Fi.' 41, incremental axial force cocfficient

versus fin deflection, M 0.5

040

OS 'IAC I a-01

Fig 4.:.lncr-emental axial force coefficiept4.0* a W ersu's fin deflection, M 01.8

03 01

021

AC.

0101

Fig. 143. IncremeriLi axial force coefficietft

9 ~J67

vgmap - 0.1" FT2

a _SF

4

SODY-WING TAIL

00.4 0.8 1.2 1.6 1.0

MACH NUMiR"

Fig 44. Pitch and yaw damping derivativesversus Mach nunmber

aJ

aI

UI

645Bll1 ,- 0A1 iI• *"1

( • ' VtNU'~l

Fig p45. Roll damplnq, derivative

2-:

O DY- | I I

U .3 e fuT A I -I N G T I

.400 6pt" -0.183 I I iI0 ______ .___S__

0.11

a .4 0.4 0.8 1.

w ,ith Fin pow~~ ersu inpich a~nd yaw

269-tiiichnm e

P OLL MOWE VM IAACIF 110"410____ 0- I CLOP

Fig 48. Roll power versuse I Mach number-

12 OOOTMSjJ I

Fig 49. Trimmed load factor and C tri

versus pitch fin daflection /ia€.,,

as ii 1

-12 ao

S:I i

-ersu- itch-fi -!flecion -

PITCH PIN ORPLI"TON IEGaP1"W

270

i-' I

APPENDIX LD

CAI-:rA-ON-L.AUJNCHED GUItWDI PROJ ECTI LES RECOMMENDEDWiNiy-l UNNU-L. 1 E:ý I PROGRAMkS

Ca nzird -coritrol lot taxed-tail design1

271

Early EDT. Winci Tunnel 'Tes for Deiign Purposesi

'Vest Outline

1. Body and Tail (controls undiflected, rollin.s & ,onrolling)

A. Test Conditions (except. a-; noted, number in parenthescs is

number of values of that variable)

1. Mach No.: 0.04, 0,A, 0.C, 0.95, 1.0, 1 ., 1.25, 1.5, 2.0(9)

2. Angles of Attack: -+60, +40, +20, .+,,, +0.50.. c, -20, _C-60, -80, -10-, -1 20, -.14-, -165°, -0'B, -20'" (le,)

3. Yaw.Angles. 0' (11

4. Roil Angles (N.A. when rolling) W., 22.50, 450, 67.5':, 90- (5)

5. Ro•W iates: d.-J/2V = 0, 0.0020, (.015, 0.020 (4)

B.NUrniw-r o01 Ruois (vise -un IHý I!.. a~l~fhynsg.m of t~i ;w

1 . Mach= 0 S. Roll Ar,.les = 0', W', 180'", 2700: 4

(correct army model asymmetir-e.ý detected.)

2. I. A. 1-5 (roling) 2'

contingency runs 13

3. I. A. 1-5 (nonrolling) 45

ctontingency runs 22

4. 'Total 111

C. Re\,i'-,; upsigr as required.

II. Body and an! td Canr-rdF (controls, .indeflc•te.()

A. test ,ond.tcons

I. - No.. 0.R, t'.9, ..95, 1.0 (4)

273

2. /-i-gles of Attack: Same a- I

3. Yaw Angles: Sarne as I (1)

4. Roll Angles: Same as I (5)

5. Roll Rat pd/2V = 0,0.015 (3)

B. Numnber of Runs

1. M = 0.8, Roll A nglecs = 0', 90', 180', 270°: 4

(correc' a symmetries)

2. II. A. (nonrolling) 20

contingency runc 10

3. II. A. (rolling) 8

contingency runs 4

4. Tota, T6

Ill. Body and TIal Canards (cntrols deflected)

A. Test Conditions

1. Mach No.: Same as l1 (4)

2. Angles of Attack: Same as 1

3. Yaw Angles: Same asl (1)

4. Roll Angles: A: Wf, 22.50, 45, 67.50, 900 (5)

B: A plus 1•2.5*, 135', 157., 0 (0)

5. Roll Rates: pd/2V = 0, 0.0075, 0.015 (3)

214

9

6. Control Deflections

a. Roll Program A at all Mach No.: (nonrc'ing)pitch: +5, -50, -7.5, -10 (4)yaw: oo (1.)

b. Roll Program A at all Mach No.: (nonrolling)pitch: 00 (1)yaw: -. 5, +50, 7.50 -,10 (4)

c. Roll Program [3 (nonrolling)Pitch: +5o, -so, -100 (3)yaw: -50, +50, +100 (3)

3. Nunlber of Runs

1. Nonr-lling

a. Pitch deflection onl y:

b. yaw deflection only:c. pit-l and yaw 80d. Total

284

2. Rollin 44a

a. Pitch '-eflection ornly:

b, yaw defleciion onlv: 32c. Pitch and yaw:

2

d. Total 72

C Revise Design as RequireaIV. Grand Tot1 1 of Runs: 7411 (minimurm)

V. General T,,t Consideraqion$

A. Test Methods

1. Six cOflponent balance.

275

'"4

2. Base pressure measurements will be taken at least at 4 points.

3. Model will represent expected flight condition (either en-graved obturator on or off).

4. Flow visualization techniques will be used.

B. Test Models/Facilities

1. 0.5 percent blockage ratio not to be exceeded at full controldeflectioiv and zero angle of attack.

2. Test Reynolds number should be as close to flight Reynoldsnumber as possible; and net below 2 x 106 (based on diameter) at Mach 1.0.

3. Facilities

a. NASA Unitary Tunnels, Ames Laboratory.

(1) High Reynolds Number. Ca., match flight on afull-scale model.

(2) A full-scale model would have less than 0,5 percentblockage ratio.

(3) Match number range is 0.7 to 1.4 in 11-foot hy 11-foot and 1.5 to 2.5 in 9-foot by 7-foot tunnel.

(4) Availablk at no cost.

(5) Availability of test time depends on nationalM . " ' Y F" ' " Ig / rIy p i:r y m e n, s G to 1 2 m o n, h w a IL.)

(6) Low number of runs pcr hour (-2)

b. CALSPAN 8-foot by 8-foot.

(1) Capable of exceeding a Reynolds number of2 x I0 throt',ghout control led flic-t Mach number regime.

(2) A full-scale model wouid have less than 0.5percent blockage ratio,

276

I.

(3) Mach number ranae •s 0.1 to 1 .3.

(4) Another tunnel is required for supersonic testing.

(5) Cost is $1500 per hour.

(6) Test time available immediately.

(7) Very high number of runs per" hour (k10) with re-

motely controlled spin and control surfaces.

c. AEDC 4T with Supersonic Blocks

(1) Capable of exceeding a Reynolds number of2 x 106 at M=1 .6 and 2.0.

(2) Blockage requirements are not limiting for super-

sonic conditions.

(3) Mach numbers are 1 .6 and 2.0.

,(,4) Ths . r, on s; d er ed the rmin -hoire tunnel for

supersonic testing.


(6) Availability of test time depends upon DOD priority.

(7) High number of runs per hour (-6) with remotely

controlled spin and control surfaces.

d. AEDC 16-foot by 16-foot.

(1) Can maintain Re = 2 x 106 (based on diameter) at

all Mach numbers up to 1.6.

(2) A full-scale model would not exceed 0.5 percent

blockage.

(3) Cost is $1400 per hour of tunnel occupancy.


* 277

--------------------------------

(5) High number of runs per hour ('6) with remotely

controlled fins and spin.

4. Models

a. Use of existing model would not allow spin control or

remote control setting of fin deflections.

b, Use of proposed 3/4 scale model would allow remotecontrol of tins but would not allow spin control.

c. (1) A model incorporating the features in (a) must bebuilt.

(2) The test time required for the transonic portion of

the final test program is probably too long at any NASA tunnel.

VI. Recommendations:

A. The NASA tunnel, have been discussed because they are available

at no cost. But if a high nationa! priority cannot be eiJblished, the time

delay in getting into these tunnels renders them useless. Therefore, it

is recommended that the CALSPAN 8-foot by 8-foot tannel be used for tran-

sonic testing (it is available on call) and the AEDC 4T with supersonic

blocks be used for supersonic testing.

B. The same order of recommendations is made for the final aero-

dynamic data package required. Scheduling will be tighter here, and the

NASA tunnels are definetely out.

C. In light of the Reynolds number problem and the final configu-

raturi aerodynamic testing required later in ED, it is recommended thatthe early ED testing be done with a full-scale, remotely controlled spin

and control surfaces model.

278

Minimum Wind Tunnel Test Program of Final Configuration:

Wind Tunnel Test Requirements.

1. Test configuration will be full-scale, preferably based on actualhardware to reduce model costs and for surface finish, and Reynolds' numbermatching.

2. Test configuration will be expected flight configuration, e.g.,obturator either on or off as intended. If obturator is on, it should beengraved.

3. All tests will be made with a 6-componet t balance plus instru-mentation to obtain hinge forces and moments on control surfaces. Basepressure will be measured.

4. The model must be capable of remote and independent control

of all control surfaces and of model 3pin rate.

5. These surface variations must be set within 0.0020 and data onall control variations and the spin rate must be available continuouslyduring a tunnel run.

6. Base pressure measurements will be taken at least at one radiusevery 90P; this radius should be half-way between the sting and the edgeof the base of the projectile. Tha pressure taps should be in the base andthe plumbing routed inboard and then out along the sting. External rakesshould not be used.

7. Data reduction will includ,! plots of all force and moment co-efficients as functions of all variables in test.

8. Flow visualization techniques will be employed at all times.

9. Read also the Early ED Test Plan. Give special attention toSection V - a discussion of Model/Facility choice.

10. If full-scale controllable model was used in early EL), the modelis already available and paid for. Any testing done in early ED on sameexternal configuration as final design doesn't have to be done again andtheir time and costs may be deducted from this plan.

279

- - - - - ~ . - -

Test Outline

I. Body Alone

A. Test Condition (number in parentheses is number of values ofthat variable)

1. Mach No.: 0.4, 0.6, 0.8, 0.9, 0.95, 1.0, 1.05, 1.1, 1.25,1.50, 2.0 (11)

2. Angles of Attack: +60, +4, +20, +1°, 0.50, 00, - 0 . 50, -1°,-2", -4°, -6°, -80, -10°, -120, -140, -I60, -180, -200 (18)

3. Roll Angles: 0", 22.50, 450, 67. 50, 90P, 180", 2700 (7)

4. Yaw Angle: 0" (1)

B. Number of Runs (considering an angle of attack sweep as onerun): 77

C. Any model asymmetries detected should be corrected and anyflow asymmetries noted for correction of data.

II. Body and Tail (rolling and nonrolling)

A. Test Conditions

1. Mach No.: Same asl (11)

2. Angles of Attack: Same as I.

3. Roll Angles: 00, 22.50, 450, 67.50, 90", 112.50, 1350, 157.5",except as noted (8)

4. Yaw Angles: 0" (1)

5. Roll Rates: pd/2V = 0, 0. 0075, 0.015, 0.030 (4)

6. Control Deflections: 0 (1)

B. Number of Runs

280

t1. p = 0, 00, 1800, 2700, M 0.8: 4 (Asymmetry check)

2. p=0: 88

3. pif0: 33

4. Tota I 125

C. Correct any model asymmetries detected in li.B.1 and note flowasymmetries.

Ill. Body and Tail and Canards (No control deflections).

A. Test Conditions

I. Mach No.: 0.4, 0.8, 0.9, 0.95, 1.0 (5)


3. Roll Angles: Same as II (8)

4. Yaw Angles: Same as 1 (1)

5. Roll Rates: Same as II (4)

6. Control Deflections: 0 (1)

B. Number of Runs

1. p 0: 40 runs

2. p 0: 15 runs

55 runs

IV. Body and Tail and Canards (controls deflected, no roll rate)

A. Test Conditions are the same as the early ED plan except MachNo. are the same as III (5).

B. Number of Runs

I 281

it

1. pitch deflection only: 100

2. yaw deflection only: 100

3. pitch and yaw: 360

4. Total 560

V. Body and Tail and Canards (controls deflected, rolling)

A. Test Conditions are the same as IV.

B. Number of Runs (same as early ED).

1. pitch deflectiononly: 40



4. Total 170

VI. Dynamic Testing

A. Test Conditions

1. Mach No.:

a. Body: Same as 1 (11)

b. Bodyand Tail: Sameasl (11)

c. Body and Tail and Canards: Same as III (5)

2. Angles of attack: Or (1)

3. Roll Angles: 0, 22.50, 450 (3)

4. Yaw Angles: 0'

5. Roll Rates: 0O

6. Control Deflections: All 0

282

VI. A. 8. Configurations: Body, Body and Tail, Body and Tail and

Canards (3)

B. Number of Runs

TOTAL: 81 1VII. Total Number of Runs

A. I: 77

B. II: 125

C. II1: 55

D. IV: 560

E. V: 170

F. V!: 81

G . Total 1149

VIII. Cost and Time

A. Model(s): $50,000 (full-scale)

+$20, 000 if two tunnels are used.

B. Tunnel Times (alternatives)

1. Ames Unitary Tunnels: 575 hours

2. CALSPAN 8'x 8' and Ames 9'x 7': 118 +32 150 hours

3. CALSPAN 8'x 8' andAEDC 4T: 118 + 16= 134 hours

C. Tunnel Costs

1. Ames Unitary Tunnels: 0

2. CALSPAN 8' x 8' and Ames 9' x 7': $177K + 0 $177K

.3

283

1* is

3. CALSPAN 8' x 8' and AEDC 4T: $177K + $12K = $189K

D. Total Costs (briodel & tunnel time)

1. Ames Unitary Tunnels: $50K

2. CALSPAN 8' x 8'and Ames 9' x 7': $247K

3. CALSPAN 8' x 8' and AEDC 4T' $259K

E. Estimated Priority Required to Obtain Tests on Time

1. High priority at national level.

2. Available immediately and high national priority.

3. Available immediately and medium priority at DOD level.

284

91

APPENDIX D

CANNON-LAUNCHED GUIDED PROJECTILES RECOMMENDEDWIND-TUNNEL TEST PROGRAMS

Fixed-wing. tail-controlled designaV

S~285

Early ED Wind Tunnel Test for Design Purposes

Test Outline

I. Body and Tail (controls undeflected, rolling and non-rolling)

A. Test Conditions (number in parentheses is number of values of

that variable)

1. Mach No. 0.4, 0.8, 0.9, 0.95, 1.0, 1.1, 1.25, 1.50, 2.0 (9)

2. Angles of Attack: +60, +4, +20, +10, +0.5, 00, -0.5o, -10, -40,

-60, -80, -100, -120, -140, -160, -180, -200 (18).

3. Yaw Angles: 00 (1).

4. Roll Angles: 00, 22.50, 450, 67.50, 900 (5) except as noted.

5. Roll Rates. pd/2V = 0, 0.015, 0.030 (3).

B. Number of Runs.

a 1. Mach = 0.8, Roll Angles = C0, 90, 1 H0°, 2/tfr: 4 (asymmetry

check)

2. Non-rolling: 45contingency runs: 22

3. Rolling 18contingency runs: 9

4. Total 98

C. Revise design as required, correct model asymmetries.

II. Body and Tail and Wing (controls undeflected, non-rolling)

A. Test conditions (except as noted).

1. Mach No. 0.8, 0.9, 0.95, 1.0 (4)

2. Same as I

. 287

3. Yaw Angles: 0' (1)

4Roll Angles: it', 22. '), 4450, 67.5 900go (5)

B . Number ot Runs (one run is. one angle of attack sweep)

1 . Mach = 0.8, Roll Angles =0*, 'ý' 1801, 270'. P (asymmetryc hec k)

2. 11. A. I1.-S5.: 20

continge~ncy runs 10

3. Total 34

C. Revise design as required (correct model aqymmetries).

Ill. Body and Tail and Wing (controls deflected, no rolling) .

A Test Conditintrs

1 . Mach No.: Same as 11 (4).

2. Angles of Attack: Same as 1.

3. Yaw Angles: 0P (1) .

4. Roll Angles: A: 0*', 22. 50, 450, 67j. 50 90" (5).

B. A plus 112.50, 135", 157.5' (8).

5. Control Deflections:I

a. Roil IProgram A at all Mach No.

pitch: +5O1 -V,5( -10", -8 PMx(£4).

yaw: OP (1).

roll: 0" (1) .

288

b. Roll Program A at all Mach No.

I[ rpitch: 00 (1).

yaw. -50, +50, +100, +1(4).SMax

roll- o0 (1).

c . RollI Proyram B at M 0. 8 and 8 R 50, Program A elsewhere.

pitch: 00 (1)I

roaw: 02' (1).c(3

d. Roll Program B at M = 0.8, Program A elsewhere.

pitch: 50 , 50, -10 (3)

Yaw: 50 +S; +10 (3)1

roll: 0- (1).

e . Roll Program B at M = 0.8, Program A elsewhere.

1 lpitch: -5', +5' (2) .

yaw: 00 (1).

roll: 50, 50 (2).

f. Roll Program B at M = 0.8, Program A elsewhere.

pitch: 0- (1) .

yaw: +50, -'5 (2).

roll: -50, +50 (2).

1t 289

2

g. Roll Program B at M = 0.8, Program A elsewhere.

pitch: +5O, -5' (2).

yaw: -5, +50 (2).

roll: -5", +5' (2).

B. Number of Runs.

1. pitch deflection only: 80


3. roll differential deflection only: 61


5. pitch and roll: 92

6. yaw and roii: 92

7. pitch, yaw, and roll: ;84

8. Total 798

C. Revise design as required

IV. Grand Total of Runs: 930 (minimum)

V. Grand Test Considerations.

A. Test Methods.

1. 6-component balance.

2. Base pressure measuremtrnts will be taken at least at 4 points.

3. Model will represent expected flight condition (either en-graved obturator on or off).

4. Flow visualization techniques will be used.

290

B. Test Models/Facilities.

1. 0. 5% blockage ratio not to be exceeded at full control deflec-tions and zero angle of attack.

2. Test Reynolds number should be as close to flight Reynoldsnumber as possible; and not below 2 x 1 0 6 (based on diameter) at Mach 1.0.

3. Facilities.

a. NASA Unitary Tunnels, Ames Laboratory.

(1) High Reynolds number - can match flight on afull-scale model.

(2) A full-scale model would have less than 0,55% block-age ratio.

(3) Mach number range is 0.7 to 1 .4 in 11-foot by 11-foot and 1 .5 to 2.5 in 9-foot by 7-foot tunnel.

t (4) Available at no cost.

(5) Availability of test time depends on national priority.(High Army priority means 6 to 12 month wait.)

(6) Low number of runs per hour (-2).

b. CALSPAN 8-foot by 8-foot.

(1) Capable of Exceeding a [Faynolds' number of2 x 106 throughout controlled flight Mach number regime.

(2) A full-scale model would have less than 0.5% block-age ratio.

(3) Mach number range is 0.1 to 1.3.

(4) Another tunnel is required for 5upersonic testing.


* 291

I

II

(6) Test time available immediately.

(7) Very high number of runs per hour (ý1 0) withremotely controlled spin and control surfaces.

c. AEDC 4T with Supersonic Blocks.

(1) Capable of exceeding a Reynolds' i~umber of

2 x 106 at M = 1.6 and 2.0.

(2) Blockage requirements are not limiting for supersonicconditions.

(3) Mach numbe, s are I A and 2.0.

(4) This is considered the main choice tunnel for super-

sonic testing.

(5) Cost is $720 pv," hour.


(7) High number of runs per hour (--z6) with remotelycontrolled spin and control surfaces.

d. AE.C 16-foot by 16-foot.

(1) Can maintain Re = 2 x 106 (based on diameter) at

all Mach numbers up to 1.6.

(2) A full-scale model would not exceed 0.5% blockage.

(3) Cost is $1400 per hour of tunnel occupancy.


(5) High number of runs per ho..jr (•6) with remot-lycontrolled fins and spin.

4. Models

a. Use of existing model would not allow spin control orremote control setting of fin deflections,

292

b. Use of proposed 3/4-scale model would allow remote

control of fins but would not allow spin control.

c. (1) A model incorporating the features in (a) must bebuilt.

(2) The test time required for the transonic portion ofthe final test program is probably too long at any NASA tunnel.

VI. Recommendations:

A. The NASA tunnels have been discussed because they are avail-able at no cost. -But if a high national priority cannot be established, thetime delay in getting into these tunnels renders them useless. Therefore,it is recommended that the CALSPAN 8-foot by 8-foot tunnel be used for

transonic testing (it is available on call) and the AEDC 4T with supersonicblocks be used for supersonic testing.

B. The same order of recommendations is made for the finai aero-dynamic data .-ckage required. Scheduf-n•"g -ill be tighter here and theNASA tunnels are definitely out.*

C. In light of the Reynolds' -lumber problem and the final configu-

ration aerodynamic testing required later in ED, it is recommended thatthe early ED testing be done with a full-scale, remotely controlled spinand control surfaces model.

ý 93)I

Minimum Wind Tunnel Test Progremr cf Final Configuration:

Wind Tunnel Test Requirements.

1. Test configuration will be full-scale, preferabLy based on actualhardware to reduce model costs and for .;urface finish, and Reynolds'number matching.

2. Test configuration will be expe.-:ted flight configuration, e.g.,obturator either on or off as Intended. If obturator is on, it should be en-graved.

3. All tests will be made with a 6-component balance plus instru-mentation to obtain hmioi forces and moments on control surfaces. Basepressure will be measured.

4. The model must be capable of remote 1nd independent control ofall control surfaces and of model spin rate.

5. These surface variations must be set within 0.002* and data onall control variations and the spin rate must be available continuouslyduring a tunnel run.

6. Base pressure measurements will be taken at least at one radiusevery 900; this radius should he half-way between the sting and the edgeof the base of the projectile. The pressure taps should be in the base andthe plumbing routed inboard and then out along the sting. External rakesshould not be used.

7. Data reduction will include plots of all force and moment co-efficients as functions of all variables in test.

8. Flow visualization techniques will be employed at all times.

9. Read also the Early ED Test Plan. Give special attention toSection V - a discussion of Model/Facility choice.

10. If full-scale controllable model was used In early ED, the modelis already available and paid for. Any testing done in early ED on sameexternal configuration as final design doesn't have to be done again andtheir time and costs may be deducted from this plan.

294

VTest Outline

I. Body A!one

A. Test Conditions (number in parentheses is number of values ofthat variable)

1. Mach No.: 0.4, 0.6, 0.8, 0.9, 0.95, 1.0, 1.05, 1.1, 1.25,1.50, 2.0 (11)

2. Angles of Attack: +6P, +40, +20, +1, 0.50, -0.50, -10, -20,

-40, -60, fo, -I100, -120, -140, -1 6, -180, -200 (18)

3. Roll Angles: 00, 9 0, 1800, 2700 (4)

4. Yaw Angle: 00 (1)

B. Number of Runs (an angle of attack sweep is one run):

1. Total 44

C. Any model asymmetries detected should be corrected and flowI asymmetries noted for data correction.

II. Body and Tail (rol!ing and non-rolling).

A. Test Conditions.

1. Mach No.: Same as I (11)


3. Roll Angles: 00, 22.5', 45, 67.50, 900 (5)except as noted

4. Yaw Angles: 00 (1) 45. Roll Rates: pd/2V= 0, 0.015, 0,030 (3)

6. Control Deflections: all 0, (1) 6 R -2', -5.° (2)

B. Number of Runs

295

1. p=0, all = 0, *= 00, 1800, 270", M =0.8: 4 (asymmetrycheck)

2. p 0, all6=0 22

3. p=0, R8 0 110

4. Total 136

C. Correct any model asymmetries detected in I1. B. 1. and noteflow asymmetries for data corrcction.

Ill. Body and Tail and Wing (no control deflection, non-roiling)

A. Test Conditions

1. Mach No.: 0.4, 0.8, 0.9, 0.95, 1.0 (5)

2. Angles of Attack: Same as I

• I•U I '• I•• ;;•' U • .. ,, ,, 0 "-'..+ '0 ^no I.. , nU ro I I-). • o Ir.) r I.1 ...

4. Yaw Angles: 0 (1)

5. Roli Rates: 0 (1)

6. Control Deflections: Same as II (1)

B. Number of Runs:

1. p= 0, al 18 = 0: 40

2. Total 40

IV. Body and Tai, and Wing (controls deflecttd, no roll rate)

A. Test Conditions are the same as the early ED plan except MatchNo. same as ill (5)

B. Number of Runs:

296

"•" Si

AV1. pitch deflection only: 100


3. roll differential deflection only: 78

4. pitch and yaw deflections: 252

5. yaw and roll deflections: 112

6. yaw and roll deflections: 112

7. pitch, yaw, and roll deflecticns: 224

8. Total 978

V. Dynamic Testing

A. Test Conditions

1. Mach No..

9 a. Body: Same as 1 (11)

b. Body and Tail: Sameasl (11)

c. Body and Tail and Wing: Same as 111 (5)

2. Rol! Angles: 0", 22.5", 450 (3)

3. Yaw Angies: 0 (i)

4. Roll Rates: 0 (1)

5. Control Deflections: A110

6. Configurations: Body, Body and Tail, Body and Tail andWing (3)

B. Number of Runs

I . Total 81

*p 297

VI. Grand Total of Runs Required

A. I 44

B. II 136

C. dIi 40

D. IV 978

E. V 81

F. Total 1279

VII. Costand Time

A. Model(s): $50,000 (full-scale)+$20, 000 if two tunnels are used.

B. Tunnel Times (alternatives):

1. Ames Unitary Tunnels: 656 hours

2. CALSPAN 8' x 8' and Ames 9' x 7' : 132 +30 162 hours

3. CALSPAN 8' x 8' and AEDC 4T: 132 +16 = 148 hours

C. Tunnel Costs

1. Ames Unitary Tunnels: 0

2. CALSPAN 8' x 8' and Ames 9' x 7' : pN.98K +0 = $198K

3. CALSPAN 8' x 8' and ALDC 4T: $198K + $12K= $21,9l.K

D. Total Costs (model and tunnel time)

1, Ames Unitary tunnels: $50K

2. CALSPAN 8' x a' and Ames 9' x 7': $268K

3. CALSPAN 8' x 8' and AEDC 4T: $280K

298

.......... . .

r. Estimated Priority Required to Obtain Tests on Time

1. High priority at national level

2. Available immediately and high national priority

3. Available immediately and medium priority at DOD level

299

DISTRIBUTION LIST

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