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AEDC-TR-74-75 AFATL-TR-74-113

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EFFECT OF VARIOUS EXTERNAL STORES

ON THE AERODYNAMIC CHARACTERISTICS

OF THE F-4C AIRCRAFT

J. M. Whoric ARO, Inc.

PROPULSION WIND TUNNEL FACILITY ARNOLD ENGINEERING DEVELOPMENT CENTER

AIR FORCE SYSTEMS COMMAND ARNOLD AIR FORCE STATION, TENNESSEE 37389

October 1974

Final Report for Period September 10 - October 13, 1973

Approved for public release; distribution unlimited.

Prepared for

AIR FORCE ARMAMENT LABORATORY (DLJC) EGLIN AIR FORCE BASE, FLORIDA 32542

NOTICES

When U. S. Government drawings specifications, or other data are used for any purpose other than a definitely related Government procurement operation, the Government thereby incurs no responsibility nor any obligation whatsoever, and the fact that the Government may have formulated, furnished, or in any way supplied the said drawings, specifications, or other data, is not to be regarded by implication or otherwise, or in any manner licensing the holder or any other person or corporation, or conveying any rights or permission to manufacture, use, or sell any patented invention that may in any way be related thereto.

Qualified users may obtain copies of this report from the Defense Documentation Center.

References to named commercial products in this report are not to be considered in any sense as an endorsement of the product by the United States Air Force or the Government.

APPROVAL STATEMENT

This technical report has been reviewed and is approved.

LAMAR R. KISSLING Lt Colonel, USAF Chief Air Force Test Director, PWT Directorate of Test

FRANK J. PASSARELLO Colonel, USAF Director of Test

UNCLASSIFIED REPORT DOCUMENTATION PAGE READ INSTRUCTIONS

BEFORE COMPLETING FORM 1- REPORT NUMBER

AEDC-TR-74-75 AFATL-TR-74-113

2. GOVT ACCESSION NO. 3. RECIPIENT'S CATALOG NUMBER

4. TITLE fand Subtitle)

EFFECT OF VARIOUS EXTERNAL STORES ON THE AERODYNAMIC CHARACTERISTICS OF THE F-4C AIRCRAFT

5. TYPE OF REPORT ft PERIOD COVERED

6. PERFORMING ORG. REPORT NUMBER

7. AUTHOR)»

J. M. Whoric, ARO, Inc.

B. CONTRACT OR GRANT NUMBERf«)

9. PERFORMING ORGANIZATION NAME AND ADDRESS

Arnold Engineering Development Center(DYFS) Arnold Air Force Station Tennessee 37389

10. PROGRAM ELEMENT. PROJECT. TASK AREA ft WORK UNIT NUMBERS

Program Element 62602F Project 2567

II. CONTROLLING OFFICE NAME AND ADDRESS

Air Force Armament Laboratory (DLJC) Eglin Air Force Base, Florida 32542

12. REPORT DATE

October 1974 13. NUMBER OF PAGES

169 14. MONITORING AGENCY NAME A ADDRESSfif dllterent /ram Contiolllni Office) IS. SECURITY CLASS, (ol thl* report)

UNCLASSIFIED 15a. DECLASSIFIC ATI ON/DOWN GRADING

SCHEDULE

16 DISTRIBUTION STATEMENT (ol this Report)

17. DISTRIBUTION STATEMENT (of the abstract intend in Block 30, II different from Report;

Approved for public release; distribution unlimited.

IB. SUPPLEMENTARY NOTES

Available in DDC

19. KEY WORDS (Continue on revere* aide If neeeaeary and Identity by block number)

F-4C aircraft wind tunnel tests transonic flow aircraft external winged stores aerodynamic characteristics scale model longitudinal stability drag characteristics longitudinal control

20. ABSTRACT (Continue on reveree side It neeeaeary and Identity by block number)

The results obtained from wind tunnel tests, which were conducted to determine the effects of external carriage of several configurations of winged stores on the aerodynamic characteristics of the F-4C aircraft, are presented and discussed. The analysis includes evaluation of the static longitudinal stability, drag, and longitudinal control characteristics of the F-4C aircraft with winged stores. Incremental drag rise and neutral-point shift associated with some of the store loadings are compared with results obtained |

.-».KIT,, 1473

UNCLASSIFIED

UNCLASSIFIED 20. Abstract (Continued)

from exisiting prediction techniques and methods. Results are presented lor altitudes of sea level, 10,000, 20,000, and 30,000 ft for aircraft center-of-gravity locations of 25, 33, and 36 percent of the mean aerodynamic chord over the Mach number range from 0.6 to 1.3 for gross weights applicable to the aircraft plus stores.

UNCLASSIFIED

AEDC-TR-74-75

PREFACE

The test program reported herein was conducted by the Arnold Engineering Development Center (AEDC), Air Force Systems Command (AFSC), at the request of the Air Force Armament Laboratory (AFATL/DLJA), AFSC, Eglin Air Force Base, Florida, under Program Element 62602F, Project 2567. The project monitor was Major Ron Van Putte. The results were obtained by ARO, Inc. (a subsidiary of Sverdrup & Parcel and Associates, Inc.), contract operator of AEDC, AFSC, Arnold Air Force Station, Tennessee. The test was conducted under ARO Project No. PA30S, and data reduction and analysis of the wind tunnel data were performed under ARO Project No. PA451. Data reduction was completed on May 17, 1974, and the manuscript (ARO Control No. ARO-PWT-TR-74-50) was submitted for publication on June 21, 1974.

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CONTENTS

Page

1.0 INTRODUCTION 7 2.0 APPARATUS

2.1 Test Facility 7 2.2 Test Articles 8 2.3 Instrumentation 8

3.0 TEST DESCRIPTION 3.1 Test Procedures and Test Conditions 8 3.2 Data Reduction and Corrections 9 3.3 Precision of Measurements 9

4.0 TEST RESULTS, ANALYSIS, AND DISCUSSION 4.1 Baseline Configuration Characteristics 10 4.2 Effect of External Stores on Longitudinal Stability

and Handling Qualities 11 4.3 Effect of External Stores on Drag Characteristics 13 4.4 Effect of External Stores on Longitudinal Control 14

5.0 SUMMARY OF RESULTS 14 REFERENCES 15

ILLUSTRATIONS

Figure

1. Wind Tunnel Installation of the F^tC with Stubby HOBOS Stores and 370-gal Tanks 17

2. Sketch of 0.05-ScaIe Model of the F-4C 18 3. Sketch of F-4C Wind Tunnel Model Wing Panel 19 4. Details and Dimensions of MAU-12B/A Pylon 20 5. F-4C, 370-gal Fuel Tank with Suspension Equipment 21 6. Details and Dimensions of the External Stores 22 7. F-4C Configuration Identification Key 31 8. Trim Stabilator Angle as a Function of Mach Number, Altitude,

and eg Location for Configuration 21 32 9. Neutral-Point Location as a Function of Mach Number and

Altitude for Configuration 21 33 10. Slope of Pitching-Moment Coefficient versus Angle-of-Attack

Curve at Trim as a Function of Mach Number, Altitude, and eg Location for Configuration 21 37

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Figure Page

11. Lift-Curve Slope as a Function of Mach Number and Altitude for Configuration 21 .• . 39

12. Trim Angle of Attack as a Function of Mach Number, Altitude, and eg Location for Configuration 21 40

13. Trim Drag as a Function of Mach Number, Altitude, and eg Location for Configuration 21 44

14. Longitudinal Control Derivatives at Trim as a Function of Mach Number, Altitude, and eg Location for Configuration 21 48

15. The Effect of the SOM Store on Trim Stabila tor Angle 50 16. The Effect of the SOM Store on Neutral-Point Location 51 17. The Effect of the SOM Store on the Slope of the Pitching-Moment

Coefficient versus Angle-of-Attack Curve at Trim 55 18. The Effect of the SOM Store on the Lift-Curve Slope at Trim 57 19. The Effect of the SOM Store on Trim Wing Angle of Attack 58 20. The Effect of the Stubby HOBOS Store on Trim Stabilator Angle 62 21. The Effect of the Stubby HOBOS Store on Neutral-Point Location 63 22. The Effect of the Stubby HOBOS Store on the Slope of the Pitching-

Moment Coefficient versus Angle-of-Attack Curve at Trim 67 23. The Effect of the Stubby HOBOS Store on the Lift-Curve Slope at Trim .... 69

24. The Effect of the Stubby HOBOS Store on Trim Wing Angle of Attack .... 70 25. The Effect of the TCTV Store on Trim Stabilator Angle 74

26. The Effect of the TCTV Store on Neutral-Point Location 75 27. The Effect of the TCTV Store on the Slope of the Pitching-Moment

Coefficient versus Angie-of-Attack Curve at Trim 79

28. The Effect of the TCTV Store on the Lift-Curve Slope at Trim 81 29. The Effect of the TCTV Store on the Trim Wing Angle of Attack .82 30. The Effect of the PF Modular Weapons Stores on Trim Stabilator Angle .... 86 31. The Effect of the PF Modular Weapons Stores on Neutral-Point Location ... 87 32. The Effect of the PF Modular Weapons Stores on the Slope of the

Pitching-Moment Coefficient versus Angle-of-Attack Curve at Trim 91 33. The Effect of the PF Modular Weapons Stores on the Lift-Curve

Slope at Trim 93 34. The Effect of the PF Modular Weapons Stores on the Trim Wing

Angle of Attack 94 35. The Effect of the Oneway RPV Store on Trim Stabilator Angle 98 36. The Effect of the Oneway RPV Store on Neutral-Point Location 99 37. The Effect of the Oneway RPV Store on the Slope of the Pitching-

Moment Coefficient versus Angle-of-Attack Curve at Trim 103

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Figure Page

38. The Effect of the Oneway RPV Store on the Lift-Curve Slope at Trim .... 105 39. The Effect of the Oneway RPV Store on the Trim Wing Angle of Attack . . 106 40. The Effect of the ERV Store on Trim Stabilator Angle 110 41. The Effect of the ERV Store on Neutral-Point Location -. . Ill 42. The Effect of the ERV Store on the Slope of the Pitching-Moment

Coefficient versus Angle-of-Attack Curve at Trim 115 43. The Effect of the ERV Store on the Lift-Curve Slope at Trim 117 44. The Effect of the ERV Store on the Trim Wing Angle of Attack 118 45. Incremental Change in Neutral-Point Location due to Various External

Stores at a Lift Coefficient of 0.2 122 46. Comparison of Measured Neutral-Point Shifts with Results from

Existing Prediction Techniques 126 47. The Effect of the SOM Store on Trim Drag 128 48. The Effect of the Stubby HOBOS Store on Trim Drag 132 49. The Effect of the TCTV Store on Trim Drag 136 50. The Effect of the PF Modular Weapons Stores on Trim Drag 140 51. The Effect of the Oneway RPV Store on Trim Drag 144 52. The Effect of the ERV Store on Trim Drag 148 53. Drag Characteristics and Drag Numbers for Various External Stores 152 54. Comparisons of Measured and Predicted Drag 154 55. The Effect of the SOM Store on the Longitudinal Control Characteristics . . 155 56. The Effect of the Stubby HOBOS Store on the Longitudinal

Control Characteristics ' 157 57. The Effect of the TCTV Store on the Longitudinal Control Characteristics . . 159 58. The Effect of the PF Modular Weapons Stores on the Longitudinal

Control Characteristics 161 59. The Effect of the Oneway RPV Store on the Longitudinal Control

Characteristics 163 60. The Effect of the ERV Store on the Longitudinal Control Characteristics . . 165

TABLE

1. Aerodynamic Coefficient Precision 167

NOMENCLATURE 168

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1.0 INTRODUCTION

The F-4C was originally designed as an air defense interceptor/air superiority fighter. The primary armament consisted of four AIM-7 Sparrow HI missiles carried semi-submerged at four fuselage stations. However, since its first flight, the F-4C has been modified to carry, launch, and/or deliver a wide variety of external stores or weapons as the Air Force, Navy, and Marines have adapted the aircraft as a multi-mission fighter.

Although the F-4C aircraft has proved adaptable to its role as a multi-mission fighter, the certification of the wide variety of weapons on the F-4C has posed problems in many areas of aircraft technology. Areas of particular concern have been the effect of external stores an longitudinal stability and drag.

Available prediction techniques have shown some success in determining these effects for conventional finned and unfinned stores. In Ref. 1, drag rise and neutral-point shifts determined from wind tunnel data were compared with results obtained from the prediction techniques of Refs. 2 and 3. Drag rise increments compared favorably; however, both techniques were limited to a maximum Mach number of 0.95 for drag rise increment predictions. Neutral-point predictions did not compare favorably, especially in the transonic Mach number range. Therefore, when the Air Force became interested in a number of conceptual winged stores, they decided that wind tunnel testing was the most reliable way of determining the effect of these stores on the aerodynamic characteristics of the F-4C. Such data were the object of the present wind tunnel test and analysis.

The tests were conducted in the Aerodynamic Wind Tunnel (4T) of the AEDC Propulsion Wind Tunnel Facility (PWT) utilizing 0.05-scale models of the F-4C aircraft and stores of interest. Data were obtained with these models at Mach numbers from 0.6 to 1.3 and angles of attack from -4 to 13 deg. In general, the stabilator angle was varied from 0 to -6.6 deg during these tests.

2.0 APPARATUS

2.1 TEST FACILITY

The Aerodynamic Wind Tunnel (4T) is a closed-loop, continuous-flow, variable-density tunnel in which the Mach number can be varied from 0.1 to 1.3. Also, nozzle blocks can be installed to give nominal Mach numbers of 1.6 and 2.0. At all Mach numbers, the stagnation pressure can be varied from 300 to 3700 psfa. The test section is 4 ft square and 12.5 ft long with perforated, variable-porosity (0.5- to 10-percent open) walls. It is completely enclosed in a plenum chamber from which the air can be evacuated, allowing part of the tunnel airflow to be removed through the perforated walls of the test section.

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The tunnel support system for the models consists of a pitch sector, strut, and sting attachment which has a pitch angle capability of -9 to 28 deg with respect to the tunnel

centerline and a roll capability of -180 to 180 deg with respect to the sting centerline.

22 TEST ARTICLES

The test articles were 0.05-scale models of the F-4C aircraft and associated stores and suspension equipment. The stores included the Stand-Off Missile (SOM), Extended Range Stubby HOBOS (ERSH), Trajectory Control Test Vehicle (TCTV), the Oneway Remotely Piloted Vehicle (RPV), and the Extended Range Vehicle (ERV). Models of several versions of modular weapons concepts were also used during these tests. These concepts were the Philco-Ford Modular Weapon Powered (PF Mod Wpns P) and unpowered (PF Mod Wpns UP) along with Rockwell International's Modular Weapon powered (NARC Mod Wpns Cls III) and unpowered (NARC Mod Wpns Cls II). All simulated rocket pods were solid allowing no flow through these pods.

A photograph of the F-4C configured with two ERSH stores and 370-gal fuel tanks is shown in Fig. 1. Figures 2 and 3 give the basic dimensions of the F-4C model and the characteristic dimensions of the wing panel. All stores were suspended from the inboard armament station (BL 4.075), utilizing the MAU12B/A pylon in the presence of the 370-gal fuel tank on the outboard wing station (BL 6.625). Details and dimensions of the pylon and fuel tank are given in Figs. 4 and 5. Sketches of the various stores are presented in Fig. 6. Configurations are identified in the configuration key presented in Fig. 7, which shows the store profiles to scale with respect to each other and assigns each configuration a number which will be used as a reference throughout the remainder of the report. The

fin orientation of the stores as carried on the aircraft is also indicated in this figure. It should also be noted that all configurations were symmetrical except configuration 24 which had only one TCTV store which was carried on the left wing.

2.3 INSTRUMENTATION

A six-component internal strain-gage balance was used to measure the forces and moments on the F-4C model. Three base pressure measurements were made using transducers and orifice tubes which extended just inside the base of the model.

3.0 TEST DESCRIPTION

3.1 TEST PROCEDURES AND TEST CONDITIONS

Force and moment data were obtained in the conventional manner by varying the

model angle of attack at a constant Mach number, Reynolds number, and stabilator angle

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setting. The unit Reynolds number was held constant at a nominal value of 5.0 x 106

per foot. The angle of attack was varied from -4 to 13 deg.

3.2 DATA REDUCTION AND CORRECTIONS

Wind tunnel force and moment data were reduced to coefficient form in the wind axis system. Base drag was calculated using an average of the three base pressure measurements along with the base area and was used to calculate forebody coefficients. However, the base drag measured in this manner was considered negligible, and therefore, all coefficients presented are measured coefficients. Corrections for the components of model weight in the axial- and normal-force directions, normally termed static tares, were also applied to the data.

The angle of attack was corrected for sting and balance deflections caused by the aerodynamic loads. The model was tested both upright and inverted to provide the data to correct for tunnel flow angularity and model-balance misalignment. Based on these data, the angle of attack was corrected for 0.35-deg upwash at Mach number 0.6 and 0.2-deg upwash at Mach number 0.8. No other flow angle corrections were made.

3.3 PRECISION OF MEASUREMENTS

The precision of the data presented which can be attributed to inaccuracies in the balance measurements -and setting tunnel conditions were determined for a confidence level of 95 percent and are presented in Table 1. The precision in setting the Mach number was ±0.002. The Mach number variation in the portion of the test section occupied by the model was no greater than ±0.005 for Mach numbers up to 0.95 and ±0.01 for Mach numbers greater than 1.0. The precision of the model angle of attack was ±0.1 deg, and the precision of the stabilator angle setting was ±0.1 deg.

4.0 TEST RESULTS, ANALYSIS, AND DISCUSSION

Included in this analysis are the trimmed aerodynamic characteristics of the F-4C aircraft for aircraft plus store gross weights representative of takeoff conditions. These characteristics were determined for altitudes of sea level, 10,000, 20,000, and 30,000 ft at eg locations of 25, 33, and 36 percent of the mean aerodynamic chord (MAC). Also included in the analysis and presented for a stabilator setting of -0.6 deg are neutral-point shifts (ANP) at a lift coefficient (CL) of 0.2 and drag data at a lift coefficient of 0.3 for subsonic Mach numbers and at a CL =0.1 for supersonic Mach numbers. Drag numbers (DN) were also evaluated and are presented with the drag data. These data are presented so that comparisons can be made with other stores using the drag index and stability number system of Ref. 2.

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The aerodynamic characteristics at trim conditions were determined from curve fits of the wind tunnel data as described in Ref. 1. The trimmed data are all presented as a function of Mach number. These data are presented for several altitudes and eg locations for the baseline configuration which is the F-4C configured with inboard MAU-12B/A pylons and outboard 370-gal fuel tanks. The data for the remaining configurations are presented and compared with the baseline configuration for several altitudes, but. only with the eg location at 0.33 MAC. Trim data at Mach number 0.6 at an altitude of 30,000 ft are generally extrapolated from the wind tunnel data. As a result of this fact, data variations for these conditions are not as well behaved as the data for other conditions.

Trimmed aerodynamic characteristics are not presented for configurations 27 and 28 because sufficient data were not taken for such an analysis.

Presented in the following sections is a discussion of the aerodynamic characteristics of the baseline configuration followed by a discussion of the effects of adding external stores to this configuration. Areas which will be discussed will be longitudinal stability and handling qualities, drag characteristics, and longitudinal control. Included in these discussions will be a comparison of the wind tunnel results with the results of existing prediction techniques for drag rise and neutral-point shifts caused by the addition of external stores to the baseline configuration.

4.1 BASELINE CONFIGURATION CHARACTERISTICS

The aerodynamic characteristics of the baseline configuration (21) are presented in Figs. 8 through 14. Trim stabilator angle (5Str), neutral-point location (NP), pitching-moment coefficient slope (Cma), and lift-curve slope (Ci,a) at trim, trim wing angle of attack, trim drag, and longitudinal control derivatives are presented in these figures as a function of Mach number. As the aircraft accelerates from Mach number 0.9 to 0.95, nose down moments and control stick movement reversal commonly known as "tuck-under" are indicated from the data in Figs. 8 and 9. This effect has been previously reported in Ref. 1. From the data in Fig. 9, one can determine the aft eg limit for takeoff as well as the changes in static margin as the aircraft accelerates through the Mach number range. In order to maintain a 1-percent MAC static margin during takeoff, these data indicate the aft eg limit to be at the 33-percent-MAC location. If the eg of the aircraft were maintained at this value as the aircraft accelerates through the transonic Mach number range, a static margin up to 10.5-percent MAC would be experienced at Mach number 0.95 at 30,000 ft. A reduction in static margin of from 3.0- to 3.5-percent MAC can be noted as the Mach number changes from 0.95 to 0.975 for all altitudes except 30,000 ft. However, since the aft eg limit of the F-4C is at 36-percent MAC, the static margin still exceeds the 1-percent MAC limit reported in Ref. 3, as the minimum acceptable stable static margin for formation flying and/or weapons delivery.

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The pitching-moment coefficient slope (Cma) and the lift coefficient slope (Ci,a) are presented in Figs. 10 and 11, respectively. The ratio of these two parameters (Cm JCia) determines the static margin, and hence, the neutral-point location can be calculated. These data indicate that the dominant parameter in determining the neutral-point location is the pitching-moment coefficient slope. The variation of neutral-point location with Mach number correlates with the variation of Cm ft with Mach number, but not with changes in CL with Mach number. For example, as the Mach number changes from 0.9 to 0.925, Cm becomes increasingly more negative, indicating an increase in static longitudinal stability (larger static margin); whereas the lift-curve slope (CL0) shows an increase which is in the direction to decrease the static margin. Furthermore, in the Mach number range from 0.95 to 0.975, Cm decreases, i.e., tends toward a smaller static margin, while C^a

decreases, which is in the direction to increase the static margin.

Figures 12, 13, and 14 show the wing angle of attack, trim drag, and longitudinal control derivatives for the baseline configuration as a function of Mach number, altitude, and eg location. These characteristics are a rather weak function of eg location. The trim wing angle of attack and trim drag show increasing values with increasing altitude, whereas the longitudinal control derivatives are relatively independent of altitude.

A2 EFFECT OF EXTERNAL STORES ON LONGITUDINAL STABILITY AND HANDLING QUALITIES

The wind tunnel data for the baseline plus store configurations were analyzed in the same manner as the baseline configuration data. The results of that analysis pertinent to the effect of the various external store configurations on the longitudinal stability and handling qualities of the F-4C are presented in Figs. 15 through 44. The plots are comparisons of the various configurations with the baseline configuration for a eg location at 33 percent of the mean aerodynamic chord.

The comparisons presented show that the addition of external stores in all cases resulted in larger stabilator deflection requirements to keep the aircraft trimmed. Figures 15 and 30 indicate that at Mach number 0.975 as much as 2-deg additional negative deflection is required to keep the F-4C trimmed when it is carrying the SOM or the PF Mod Wpns stores than is required without stores. Again as for the baseline configuration, the increase in stability noted in the transonic Mach number range coupled with the larger required control stick movement to keep the aircraft trimmed indicates that adding external stores to the baseline configuration aggravates the tuck-under noted for the baseline configuration.

In addition to tuck-under, the change in the static margin with Mach number is another factor that affects the handling quality of the F-4C. The addition of the various external

11

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stores to the base-line configuration had primarily two effects on the static margin changes with Mach number.

In the first place, the data in Figs. 16, 36, and 41 show that the SOM, the RPV,

and the ERV stores reduced and smoothed the static margin changes with Mach number in the transonic Mach number range. Secondly, the data for the ERSH (Fig. 21), the TCTV (Fig. 26), and the PF Mod Wpns stores (Fig. 31) show that, at certain altitudes

as the Mach number changes from 0.9 to 1.0, the static margin first increased sharply and then decreased abruptly to about the subsonic value.

These data imply that, when the F-4C is carrying the Stubby HOBOS stores, the TCTV store, and the Philco-Ford Mod Wpn stores, the aircraft eg location must be chosen

carefully to provide the required stable static margin for weapons delivery.

At Mach numbers from 0.6 to 1.0, the addition of external stores to the baseline configuration was destablizing in all cases. Neutral-point shifts up to 4-percent MAC (Fig. 36) were experienced at Mach number 0.6 when the RPV stores were added to the baseline configuration, whereas when the other store configurations were installed, the neutral-point shift varied from 1- to 3-percent MAC in the low subsonic Mach number range. At the supersonic Mach numbers, the effect of the stores on stability is not as well defined, but in general, the data show the stores to be less destabilizing in this Mach number range. In fact, at H = 30,000 ft, the data (Figs. 16, 21, 26, 31, 36, and 41) show that the addition of external stores produces an increase in stability at Mach numbers 1.05 and 1.1 for all configurations except for configuration 24 (TCTV). These trends in stability variation with Mach number, as in the case of the baseline configuration, can be correlated with the changes in Cm that resulted from the addition of the external stores to the baseline configuration. The increase noted in trim wing angle of attack when stores were added to the baseline configuration (Figs. 19, 24, 29, 34, 39, and 44) is primarily a result

of the gross weight increase due to the stores.

Presented in Fig. 45 is the neutral-point shift due to the addition of the various external stores to the baseline configuration calculated for a lift coefficient of 0.2 and stabilator setting of -0.6 deg. As stated previously, these data are presented so that the effect of the external stores on aircraft stability can be evaluated using the technique of Ref. 2. These data show a large shift in the neutral-point location due to the addition of pylon-mounted external stores in the transonic Mach number range. A destabilizing

shift of up to 8-percent MAC is noted for some configurations. This forward shift generally peaks out at Mach number 0.925 and is generally followed by a sharp aft shift as the Mach number increases to 1.05. The exception to this trend is configuration 24 (TCTV). However, it should be emphasized that only one store was present on"the aircraft for that configuration.

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A comparison of the change in neutral-point location (ANPx) at M,. = 0.85 determined from the data in Fig. 45 with the empirically determined prediction curves of Ref. 2 is shown in Fig. 46a. The data show measured forward neutral-point shifts of up to 2.5-percent MAC larger than would be predicted using the finned store prediction curve of Ref. 2.

Figures 46b, c, and d compare the neutral-point shift at trim with the neutral-point shift at trim predicted using the method of Ref. 3. This prediction technique which is a semi-empirical technique is more general than that of Ref. 2 in that it allows for predictions over the entire Mach number range from 0 to 2.0. These data show that the Ref. 3 technique under-predicts the forward shift of the neutral point due to the addition of the external stores in the subsonic Mach number range by 1- to 2-percent MAC. In the Mach number range from 0.9 to 1.0, the discrepancy between measured and predicted values generally increased. For example, a difference of about 5-percent MAC is indicated at Mach number 0.925 for configuration 30. For Mach number 1.0 and above, the trends are not well defined.

These comparisons show similar results to that reported in Ref. 1 where the largest discrepancies between predicted and measured values of neutral-point shifts were in the transonic Mach number range.

4.3 EFFECT OF EXTERNAL STORES ON DRAG CHARACTERISTICS

The effect of the addition of various external stores on the trim drag characteristics of the baseline configuration is presented in Figs. 47 through 52. In these figures, the data are presented as a function of Mach number and altitude for a eg location of 0.33 MAC. These data show that at a given altitude, the addition of external stores to the baseline configuration increases the trim drag by approximately a constant increment. Larger incremental increases in trim drag are generally noted supersonically than are noted subsonically. Configuration 22 (SOM stores) exhibits the highest trim drag, whereas configuration 23 (Stubby HOBOS) exhibits the lowest trim drag (Figs. 47 and 48).

Figure 53 presents the drag data evaluated at lift coefficients of 0.3 for subsonic Mach numbers and 0.1 for supersonic Mach numbers for a stabilator setting of -0.6 deg. By using these data, as outlined in Ref. 2, the drag number for the various stores was evaluated and is shown on these plots. This number is currently used by operational units to assess the performance of the F-4C when loaded with stores. A comparison of the drag number shows that the SOM store contributes the largest increment of drag to the baseline configuration, while the ERSH store contributes the least amount of drag. This is consistent with the results of the trim drag presentation discussed previously.

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Comparisons of measured and predicted values of trim drag are presented in Fig. 54 for configurations 23, 24, and 30. By using the method of Ref. 3, these data show that higher values of drag would have been predicted than were measured with the difference being approximately a constant value for all Mach numbers. Lower values of drag are predicted than measured using the method of Ref. 2 over the Mach number range from 0.6 to 0.9. However, for Mach numbers from 0.9 to 0.95, agreement between measured and predicted drag values is good except for configuration 30 for which higher values of drag would be predicted than were measured. Overall, both prediction methods do remarkably well in predicting the drag of these three configurations.

4.4 EFFECT OF EXTERNAL STORES ON LONGITUDINAL CONTROL

Longitudinal control derivatives, Cm,, (elevator power) and Q. (elevator lift effectiveness), are presented in Figs. 55 through 60 as a function of Mach number and altitude for a eg location of 0.33 MAC. The data in Fig. 55 show that there is a reduction in elevator power and elevator lift effectiveness in the Mach number range from 0.9 to 1.0 when the SOM store is installed on the baseline configuration. Over this same Mach number range, the addition of the Stubby HOBOS store and the ERV store produced a decrease in the elevator lift effectiveness without significantly affecting the elevator power (Figs. 56 and 60). The data in Fig. 57b show that the TCTV store produces an increase in the elevator lift effectiveness subsonically and supersonically, whereas a reduction is noted over most of the transonic Mach number range. In general, there appears to be ample elevator power available when the aircraft is carrying these winged stores.

5.0 SUMMARY OF RESULTS

Wind tunnel tests were conducted to determine the effects of external carriage of several configurations of winged stores on the aerodynamic characteristics of the F-4C aircraft. Results of these tests may be summarized as follows:

1. The data presented show that the tuck-under characteristics of the baseline configuration are aggravated when winged external stores are added to the configuration.

2. The addition of the Stand-Off Missile, the Oneway Remotely Piloted Vehicle, or the Extended Range Vehicle stores to the baseline configuration reduced and smoothed the fore and aft shifting of the neutral-point location that occurred in the transonic Mach number range.

3. The addition of the Extended Range Stubby HOBOS, the Tactical Control Test Vehicle, or the Philco-Ford Modular Weapons stores to the baseline

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configuation resulted in larger fore and aft shifts of the neutral point. For certain altitudes as the Mach number changed from 0.9 to 1.0, the static margin first increased sharply and then decreased sharply to about the subsonic value.

4. The addition of the Stand-Off Missile stores to the baseline configuration produced the largest increase in drag coefficient, whereas the addition of the Extended Range Stubby HOBOS stores resulted in the smallest increase in drag coefficient.

5. There was some loss of elevator power and elevator lift effectiveness in the transonic Mach number range when the stores were added to the baseline configuration; however, adequate elevator power was available to keep the aircraft in trim for the conditions analyzed.

6. Incremental drag rise predictions utilizing current prediction technique» compared favorably with measured values; however, neutral-point shift predictions did not compare favorably with measured values especially in the transonic Mach number range.

REFERENCES

1. Whoric, J. M. "Effect of Various External Stores on the Static Longitudinal Stability, Longitudinal Control, and Drag Characteristics of the F-4C Airplane." AEDC-TR-73-186 (AD914456L), November 1973.

2. Weber, William B. "Effect of External Stores on the Stability, Control, and Drag Characteristics of the McDonnell Douglas F-4 Aircraft." Aircraft/Stores Compatibility Symposium Proceedings, Vol. Ill, Eglin AFB, 1969, pp. 28-54.

3. Dyer, R. D. and Gallagher, R. D. "Technique for Predicting External Store Aerodynamic Effects on Aircraft Performance." Vol. 1, Dayton, Ohio, 1972, pp. 115-141.

15

4

v * 4 4 * 4 . 4 •A

4 "A t ■•• "j ■ 4 3» 4 * 4-4,4

4 -A -^ ■* .^ 4 » x% «i .

4 4 ,v» 4 *

4 Ä

* 4 .* *

4 v" * 4 ^ - 4 4

* 4 4 ^ ^/^ * *

4

4

^> 4 * * * 4

* 4 * ,»

«* 4 4 4 4 4 4 4 <* 4 4> 4 ' 4 4 4 4 4 4

<4 4 4 4 4■ % 4 '4.. 4 * 4 ■ d 4 * 4 444«*

Figure 1. Wind tunnel installation of the F-4C with Stubby HOBOS stores and 370-gal tanks.

> m D O

•si 01

AEDC-TR-74-75

WL 0 000

BL-I 1.560-

FS-IJ35

STATIONS IN INCHES

BL 11.360-

Figure 2. Sketch of 0.05 scale model of the F-4C.

18

AEDC-TR-74-76

ALL DIMENSIONS IN INCHES

T-FS 7.517

-AREA BLANKETED BY FUSELAGE AND NACELLES

FS 10.566

FS 13.041

MAC (THEORETICAL)

MAC (EXPOSED)

0.580

0.230

Figure 3. Sketch of F-4C wind tunnel model wing panel.

19

O

FS 11.55

WING CHORD

WL

BL

0.250-

4.075

¥ SUSPENSION- POINT SUSPENSION POINT


> m a o

Figure 4. Details and dimensions of MAU-12B/A pylon.

BODY CONTOUR. TYPICAL BOTH ENDS

STATION BODY OIAM STATION BODY «AM

0.000 0.000 2.500 •. tie 0.025 0.100 t.750 1.156 0.050 0.144 5.000 1.190 0.150 0.258 9.250 1.218 0.250 0.S40 3.500 1.242 0.500 0.498 3.750 I£b0 O.TSO 0-622 4.000 1.274 1.000 0.724 4.250 1.286 1.250 0.812 4.500 1.294 1.500 0.890 4.750 1298 I.TSO 0.958 5.000 1300 2.000 1.016 6 000 1.300 2.250 1.070

NOTE: MODEL STATIONS AND DIMENSIONS IN INCHES

Figure 5. F-4C, 370-gal fuel tank with suspension equipment.

> m □ o

to

TANGENT POINT

LUG-^

D O ■H a ■ii


a. Stand-off missile (SOM) Figure 6. Details and dimensions of the external stores.

to

~f 1.100 ,

I 0.375y^

\

T T S"

I i

0.40O, T .800

.138

•—1.850—4* 4 -0.700

-4.028- 4.181-

4.950-

too, r —-4-0.8« 71 i T 30'


b. Extended Range Stubby HOBOS (ERSH) Figure 6. Continued.

m ü o

Ol

> m o o

s

.050

0.375R

0.625 FE

x Z7

30J K-I.I54

80 •) -1.780

— 3.225

4.725

4.929-

7.246-

»Mv/

■ 7.333- • 7.449-

1.500

0.800 I 500

0.900D


c Tactical Control Test Vehicle (TCTV) Figure 6. Continued.

to

99.6—

k-1.soo—•)

I.-0.62S ^\>

-0.750D ^

1*0.150 D 1 (TYP»

•-0.3750

•—i.'eea—•!


d. Philco-Ford Modular Weapons Powered Figure 6. Continued.

> m o O ■H JO

■si Ul

ON

. ■*) LO.ISOD 45« ' ' (TYP)

> m a o ■H 30


e. Philco-Ford Modular Weapons Unpowered Figure 6. Continued.

i. I 0.520 -LUG <^-

0.300R

^

•-1.190^1 •-I.260H

0.25 ur^:

-2.270— 2.650 ■ 2.900 — 3.500

— 3.750- 4.120-

4.410 — —5.010-

5.300— — 5.550-

5.800- — 5.850-

rl.940

0.3600 T

0.680 D 0.5000 0.160D


f. Rockwell International Modular Weapons Class III Figure 6. Continued.

> m D o

a)

to 00

0.9000 0.8500 0.580D

> m □ o ■ H a ■il


g. Rockwell International Modular Weapons Class II Figure 6. Continued.

illis 600D 2300


h. Oneway Remotely Piloted Vehicle (RPV) Figure 6. Continued.

> m O O ■H X

o

-3.220 J

L5S-

4.100- 7.250-

7.420-

K0.900D h-0.8000


> m

n H DO

Extended Range Vehicle (ERV) Figure 6. Concluded.

AEDC-TR-74-75

NOTE' PYLONS ARE SHOWN OH AIRCRAFT PROFILE OMLY TO INDICATE ARHAMEhT STATIONS

CONFIO NO

EXTERNAL ARMAMENT

ARMAMENT PROFILE I !

ARMAMENT STATIONS

370 QALLON FUEL TANK

370 GALLON FUEL TANK

Ü £ 370 GALLON FUEL TANK

Ü Ö

370 OALLON FUEL TANK

b


PFMOO WPNS POWERED

Ü Ö

370 OALLON FUEL TANH

PF MOD WPNS UNPOWERED Ö Ö


NARC MOO V CLASS m Ö Ö

370 GALLON FUEL TANK

NARC MOD WPNS CLASS 0 Ö Ö


Ö Ö


Ü Ö

Figure 7. F-4C configuration identification key.

31

AEDC-TR-74-75

SYN CONFIG STORE CM CG □ 21 PTL0NS+370TRNKS 483!1 25C O 21 PYLONS*370TANKS 4831! 33C A 21 PYLONS*370TANKS 48311 36C

-10

-8

-6 Sir

-4

H=30.000

<F=3 —-<M^|Z 1

H=20.000

.000

ij *-. ■WH 1 na £> -H Hj N *£ Sj 15 s s: -J 1

r- —— d Id {-i i I-

H= SE n i

-6 Sir

-4

0

-8

-6 •sir

-2

0 6 7 8 9 10 11 12 13 14x10-«

Figure 8. Trim stabilator angle as a function of Mach number, altitude, and eg location for configuration 21.

r n K~ ■»» ■•-■ •H W H j? m s b rj 1

t= ■— —— =i n 1=4 r* H ■M —■

32

AEDC-TR-74-75

SYM CONFIG STORE CM CC

O 21 PYL0NS*370TANKS U8311 33C

H*SEA LEVEL

CR — — 3D

34 —

tf\ .... au

4D "" ""

NPIXC) Ml

4c "" "~ - It-, " . 3-13 it 1 - 3£S/ ^Q - —.... 1 1 .._ . / ¥ Jo ™J" /

--it - [ .Z-t^t It -,,,,. -os o-=*>

3HO- —™",s

JU

oc «d

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3

a. 1-1= Sea level Figure 9. Neutral-point location as a function of Mach number

and altitude for configuration 21.

33

AEDC-TR-74-75

STM CONFIG STORE CM CG O 21 PYL0NS*370TRNKS 48311 33C

62

58

54

50

46 NPCCCI

42

38

34

30

H-10.000

26

1 L 1

• o

i

! f\ ' i

! / /

uk C) ! i Q) "1[ /

/ \/ i

/ I i

.y.-<jy-f TrT 1 1 ' Vi"l'T~l ■ HI''

. 1 1 .

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3

b. H = 10,000 Figure 9. Continued.

34

AEDC-TR-74-75

STM CONFIG STORE GW CG 0 21 PYL0NS*370TflNKS 48311 33C

H=20.000

CO 30

Cll — — 34

DU '•/

M\

LIC —— ' !■

40 1 NPi*n

1c *" p* / \ Cfj

t-& t- 9Q _ I Vv 3D ~~ 5 3 i 33 *>-52- Ql 1 . k_ aa C "" 34 < ^~

QH JU

oc 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3

c. H = 20,000 Figure 9. Continued.

35

AEDC-TR-74-75

SYM CONFIG STORE CM CG

O 21 PTL0NS*370TfiNKS «18311 33C

62

58

54

50

46 NPIJE)

42

38

34

30

H=30.000

26

— —- — — —- — — — — — —»■ ■■ —. — — _ _____ ___.._. .-jr

— — — — — — —— — —■■ ■—— — — — — — — — — — —— — -—^ — — —

— _ _— _ — —— _ — — — —, — — _ _— _ _ _— —. _ _ _ ^L — — ——. ■—t

—. _ _—. — _ _ — — __- — — — — — —- — — _- --* ... i—j^, _ __ —„ _ __, _

— _— — — — — — — — — — — — — — — — — — —J| X - — —I M —_ __ _ »

^I^EMIIIIIXX:::::::,:

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3

d. H = 30,000 Figure 9. Concluded.

36

AEDC-TR-74-75

STH CONFIG STORE CM CG D 21 PYLONS*370TRNKS 48311 2SC O 21 PYLONS*370TRNKS 48311 33C A 21 PTLONS*370TflNKS 48311 36C

C-

0.004 H=10,000

n' s o,

-0.004 I

EAAQ

l— —

-0.008 —— —< H \

\ I la -0.012 \r s

K v-

-0.016 s ■*<r-

*s s^

-0.020 ^*< >>

-0.024 H= =SE :« LEV

0.004

0

-0.004

C* -0.008

'- '^,_ "=—<ngr.

50 ,,_ D SB c ^±;_ £^ C* >S^^ 50 ^^^ ^^ w ^^ k^ ^r-

^L-

-0.012

-0.016

-0.020

-0.024 l

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

a. H = Sea level and 10,000 Figure 10. Slope of pitching-moment coefficient versus angle-

of-attack curve at trim as a function of Mach number, altitude, and eg location for configuration 21.

37

AEDC-TR-74-75

SYM CONFIG STORE CM CG □ 21 PTL0N5*370TRNKS «48311 2SC O 21 PYL0NS*370TANKS 48311 33C Ä 21 PYL0NS*370TANKS 48311 36C

H: '30.000

o'

"-« >— »■■ -*1

-0.004

-0.008 Ö A

Ss.

-0.012 T k"

-0.016 Irk T»

r*

-0.020 1Q

-0.0211 H=20.G 00

0.004

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4 1.

b. H = 20,000 and 30,000 Figure 10. Concluded.

38

AEDC-TR-74-75

STM CONFIG STORE GH CG 0 21 PYLONS*370TRNKS 48311 33C

0.10

0.09

r 0.08

0.07

0.06

0.05

0.09

C,. 0-08

0.07

0.06

0.05

0.09

CL. 0-08

0.07

0.06

h 1=30.000

9K / %

ÖN> A A *

S Sy

i

<r" **

Y 0 >0 .000 1— i

i i R mJ \

/ \ P ~~

<H M ^ i y —■

h ■» 10 .000

0.05

35 Pr

H=SER LEVEL

6 7 8 9 10 11 12 13 14xlQ-> M. 'cc

Figure 11. Lift-curve slope as a function of Mach number and altitude for configuration 21.

39

AEDC-TR-74-75

STM

□ O

CONFIG STORE GW CG 21 PYL0NS+370TANKS 48311 25C 21 PYL0NS*370TfiNKS 48311 33C 21 PYL0NS*370TflNKS 48311 36C

H= SEfl LEVEL

3

8

7

6

w tr 5

4 1 1, 1 ^ fc>.

>* ^

2

^j N L s N LB

■ ^ r®8 «0. —* k— «MM ■M* "-rf I 1

n 1 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

a. H = Sea level Figure 12. Trim angle of attack as a function of Mach number,

altitude, and eg location for configuration 21.

40

SYM CONFIG STORE GH CG H 21 PTL0NS+370TRNKS 48311 25C O 21 PYLQNS*370TflNKS 48311 33C A 21 PYL0NS+370TftNKS 48311 36C

AEDC-TR-74-75

10 1 ■\= 10.000

g

8

7

6

w tr 5|

4

3

2

■ 1

n 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

M, CO


41

AEDC-TR-74-75

SYM CONFIG STORE GW CG Q 21 PYL0NS*370TflNKS M8311 25C O 21 PYL0NS*370TflNKS 48311 33C A 21 PYL0NS*370TfiNKS y8311 36C

1 n HS ; ?0.000

Q a

8

71

6

"w tr 5

4

3 QQ.

2

i l

0 -

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4


42

AEDC-TR-74-75

STH CONFIG STORE GH CG □ 2! PYL0NS+370TflNKS 118311 25C O 21 PYL0NS*370TANKS 48311 33C A 21 PYL0NS*370TflNKS 48311 36C

1 H= 30.000 l0v A M

\

-t \

■

b " \

"st - 5 vH.

H

Q — J

*» C

1 1

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4 Moo


43

AEDC-TR-74-75

SYM

CD O

CONFIG STORE GH CG

21 PYL0NS*370TPNKS U8311 25C 21 PYL0NS+370TANKS »18311 33C 21 PYL0NS*370TflNKS 48311 36C

H=SEfl LEVEL u. \c

nil U. 11

n in u. 1U

n no u.ua

0.08

0.07

0.06

0.05 J 0.04 f J i 0.03 1 1=L ^ r sat SBS «4 M

0.02

0.01

0 0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

Hoc

a. H = Sea level Figure 13. Trim drag as a function of Mach number, altitude, and

eg location for configuration 21.

44

SYM CONFIG STORE GW CC Q 21 PYL0NS*370TRNKS U8311 25C O 21 PYLCNS*370TfiNKS W311 33C A 21 PYL0NS*370TfiNKS 48311 36C

AEDC-TR-74-75

0.12

0.11

0.10

0.09

0.08

0.07 Cotr i m

0.06

0.05

0.04

0.03

0.02

0.01

H=10.000

.

■

J t [ J i

*"< [^5 sss =S| W r

... 0.5 0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 1.4

45

AEDC-TR-74-75

STM CONFIG STORE GM CG G 21 PYLONS*370TPNKS 48311 2SC © 21 PYLQNS*370TANKS 48311 33C A 21 PTLONS*370TRNKS 48311 36C

H=20.000 U. l£

n 11 u. 11

0.10

0.09

0.08

0.07 cDtrim

0.06 A PS ss= = =4 1

f s^1

0.05 1 k A r

N L 4 0.04

\ **, N N I, - P*

0.03 T M

0.02

0.01

0 -

0.5 0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 1.4

46

STM CONFIG STORE GM CG E 21 PYL0NS*370TRNKS ¥8311 25C O 21 PYL0NS+370TANK5 «8311 33C A 21 PTL0NS*370TfiNKS 48311 36C

AEDC-TR-74-75

0.12

0.11

0.10

0.09

0.08

0.07 c0trim

0.06

0.05

0.04

0.03

0.02

0.01

H=30.000

' J \

\ v\

^\

•

0.5 0.6 0.7 0.8 0.9 1.0 1.1 Mcc


1.2 1.3 1.4

47

AEDC-TR-74-75

STM

□ CONFIG STORE CM CC

21 PYLONS*370TflNKS M8311 2SC 21 PYL0NS*370TRNKS U8311 33C 21 PYLONS*370TANKS 18311 36C

0 H=30.000

r -o.ooy

_n nnOi -U.UUO( >- —* •—■> -« J-fl Tt Ü i r- _n ni3< F HM —i ^ >) ^ ^ -U.UJe n n *l P- **

-0.016

0 H=20.O00

r -o.oou. cn6s

_n ft/id -U.UUO|

-0.0121 ö -0.016

0 H=10 .000

„ -0.004 ClißS

-0.008

-0.012*

-0.016

0 H=SE R LEVEL

r -O.OOil

-0.008

-0.0125

-0.016 5 7 3 9 1 0 1 1 1 2 1 3 1 11x10-»

a. Stabilator power Figure 14. Longitudinal control derivatives at trim as a function of

Mach number, altitude, and eg location for configuration 21.

48

AEDCTR-74-75

SYM CONFIG STORE GN CG O 21 PYLONS* 370TANKS 116311 25C © 21 PYL0NS*370TPNKS W311 33C A 21 PYL0NS*370TRNKS 48311 36C

0.012 H»30.000

„ 0.008; cL6s

n nou ( Q 8^ 1 U.UU4■

J 0

0.016

pff 1 H=20 .000

r 0.012 cL6s

n nno

-* M H a k B id 9 -J is a U.UUU(=

1 »

o.oou 1 1 I

0

0.012 H»10.000

„ 0.008* CL6S 5

O.OOiJ

\-

0

0.012 H=SER LEVEL

„ 0.008, cL6s

0.0011

p« A B ft -4 14 Ä ^ U m *■ 1

0 5 7 3 3 1 0 1

1> 1

>

1 2 1 3 1 •IxlO-'

b. Stabilator lift effectiveness Figure 14. Concluded.

49

AEDC-TR-74-75

STH CONFIG STORE CM CC

0 21 PTLONS*370THNKS 4831! 33C O 22 ' SON 52311 33C

-10 H»30.000

-8

-6 Mi «N., fci ITD- O.

T IT

-4.

-2

0 H=20.000

-6 »ttr

-II

-2

U |

J3|

H= 10 .0 00

Figure 15. The effect of the SOM store on trim stabilator angle.

50

AEDC TR-74-75

SYM CONFIG STORE GH CG O 21 PTL0NS+370TRNKS 483!1 33C O 22 SOM 52311 33C

H-SER LEVEL

TT | i I »Jg — ,., ._!__ .. _._♦_.. — i j i ' A \ D4 f "" "" ~ jf

Jrl

2 A

VJU ■ ■"•- • " \/> j J^^

<r^ ' t/' ! 4Ö ~"~" ' ' ""*"" Xr r

MPOCCI J7 IB Ap

<iC — "" ——— —— —— -1 ^ JL \-jr 3 D/

JO — — — — — — «|

™

' -nr-O-^M IH 1

3U ~ ~~

oc 1 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3

a. H = Sea level Figure 16. The effect of the SOM store on neutral-point location.

51

AEDC-TR-74-75

STM CONFIG STORE GN CG Q 21 PYL0NS*370TANKS 48311 33C O 22 SOU 52311 33C

H*I0.000

Do — "■ ~" —*~

CII _ _ II 34 ^T~

■

en — — _ ___ . „ ., j.

/\ y

4U " """■ '""fj" "

»PIZCI

in \ß)/i

4c ' | T |«| ^T if

[ i\ i op . ,._ ..__ ... ._ / l \ fl Jo

—1

aiilfc-""- "" . f^i 04 ^ ~

4 1

on .., ■ . i

JU

oc L 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3

Mec


52

AEDC-TR-74-75

SYN CONFIG STORE GH CG

Q 21 PYLONS*370TflNKS 48311 33C G 22 SOM 52311 33C

H*20.000 o* -- —

Do — ~~f—

D4 —

en . - , _ i 3U ^^ f

i y

mj __f__ -

NPI5E) 1

4c "" "~ v" m # > x

OQ 1 1 J tr I I JO

/ /

dm»-""17

w.^""!""* an JU —*

1

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 Moo


53

AEDC-TR-74-75

SYM CONFIG STORE CM CC □ 21 PYL0NS+370TflNKS 48311 33C O 22 SOU 52311 33C

H=30.000 o£ — -r- —

au — —1~~ " y '■■■ ■ — • ■■" ■■* ■

o4 ■ * "" ' s* LJ' jr y

if f

«>U "' | ~ " / f |

1 /I / I / ' IJ

'Wf 1 NPJ7C1 ilvC

4cT —' "" " "Ja j/*~ " ~ — — / J/ / i ö

■5R . i — ... , (a i _ JU *— / 7* ,' 7

□ ( 34 jr / -"^ 5/ ++ 3U *-

oc 1 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3

K 'oc


54

AEDC-TR-74-75

SYM CONFIG STORE GH CG Q 21 PTL0N5*370TflNK$ «4831! 33C

22 SOU 52311 33C

0.004

-0.004

-0.008

-0.012

-0.016

-0.020

-0.024

0.004

-0.004

H*10.000

u \0(

.

H=SER LEV

-0.008

<H4— < h*L_

Q A fe£/^

■v ^ -N, ^n

b

-0.012

-0.016

-0.020

-0.024 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

a. H = Sea level and 10,000 Figure 17. The effect of the SOM store on the slope of the pitching-

moment coefficient versus angle-of-attack curve at trim.

55

AEDC-TR-74-75

STM CONFIG STORE CN CC Q 21 PYLONS*370TRNKS 48311 33C O 22 SOH S23I1 33C

0.004 M=30.000

-0.004

c*. -0.008

-0.012

-0.016

-0.020

-0.024

0.004

0

-0.004

-0.008

-0.012

-0.016

-0.020

Ö

■?r

N V

H »2C 1.000

-0.024

1

*—«SSt. _JE(JQ

ÖU 3^ ^^ äs

i

E 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

b. H = 20,000 and 30/000 Figure 17. Concluded.

56

AEDC TR-74-75

iW 1/

Mil- •^-^^.,

—

£ - —

i i 1

1 .

H=20.000

SYM CONFIG STORE CM CC G 21 PYL0NS*370TANKS 48311 33C 0 22 SOM 52311 33C

H=30.000 0.10

0.09

r 0.08

0.07

0.06

0.05

0.09

C^O.08

0.07

0.06

0.05

0.09

CL. 0.08

0.07

0.06

0.05

0.09

C,. 0.08

0.07

0.06

0.05 6 7 8

Figure 18. The effect of the SOM store on the lift-curve slope at trim.

i i

t i

1

nl r*f *]

f\ «ü J s r r^

ET t

! i 1 i i i

I j I i t !

i

1- 1=1 0 .01

:a fir

H=SEA LEVEL

tt i H

J r?w N IN \si = 4 r^ T •*, I r*

I . 9 10 11 12 13 14x10-1

57

AEDC-TR-74-75

SYM CONFIG STORE GH CG Q 21 PYLONS*370TANKS 48311 33C O 22 SOM 52311 33C

in 1 1« ' 5EP LEVEL

1U

Q y

8

7

"6

*w tr 5

4

3

2 J^I of

i ■"Ö-

l

n 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

a. H = Sea level Figure 19. The effect of the SOM store on trim wing angle of attack.

58

AEDC TR-74-75

STK CONFIG STORE CH CC □ 21 PTLOMS*370TfiNKS 48311 33C 0 22 SOM 52311 33C

i n 1 1« 10.000

1U

Q y

8

7

6

"w tr 5(

4

3

2 or "O»

i3>f yQs ""O-

i -

l

n 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4


59

AEDC TR-74-75

STM CONFIG STORE GM CG

0 21 PYL0NS*370TflNKS M8311 33C O 22 50M 52311 33C

1 ri= , 20.000

9

8

7(

l\ 6 \

\S w tr 5

\

U i\ j

3 Jn.

2

l_ft| jT-^ ^O-

i | l

0 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4


60

AEDC-TR-74-75

STH CONFIG STORE CM CC D 21 PYL0NS*370TRNKS M.8311 33C O 22 SOM 52311 33C

i n \ is 30.000

o y

8

7 .

6

w tr 5

|f 1 ^L

H TTväLEl

3 uk

N > 2

t| J

i 1

n 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4


61

AEDC-TR-74-75

SYM CONFIC STORE CH CC D 21 PTL0NS«370TRNKS H8311 33C O 23 ERSH «9683 33C

H=30.000

c ... ,Jb Ss^ _ JL s* jß g3i==^^h

^3T -«jF^-^

o L-U-LLLJJJ H=20.0C

-8

-6 Slr

-2

0

-8

•atr

-2

0

-8

-6 Str

-4

-2

0

,. Xiie "^=5*^

H=10.0(

,/ £ ft H< H F

L> <3| K H— -: ^ I IM ■■ =-< H

H= SE fl 1

j feP xa d H 0 m

^| d I IH M i i—. ^ »*

.

6 7 8 9 10 11 12 13 111*10-»

Figure 20. The effect of the Stubby HOBOS store on trim stabilator angle.

62

AEDC TR-74-75

SYM CONFIG STORE CW CO 0 21 PYLONS*370TANKS »48311 33C O 23 ERSH »49683 33C

H«SEfl LEVEL

f ■ ■ ■ — ' Do — — — —I—

i i" iiii 34 — — ■ | "" — "~ —

Sy SA

rn i , ! J JT*. 3U ^^

Jcjf jT j[\

r s 40 ~t—) ~" ™ \/ 1>

NPttCJ J y^ *tr

/* 4c ~ ~ D—(T —

->o ,_, .1. *,.. , /|/ i rn i 3D yg \ld

r sv I'll

341»- — r™ -^pT1

( ^- — — -~ ""*""

JU ~ "" "" "

oc L 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3

a. H = Sea level Figure 21. The effect of the Stubby HOBOS store on neutral-point location.

63

AEDC-TB-74-75

SYM CONFIG STORE GH CG

□ 21 PYLONS+370TRNKS «8311 33C O 23 ERSH 149683 33C

H=l0.000

3D — " "'" "" ~*~

111 — — - ~J— 04

1 > ' j en - .i—1 . ,_i i JU f | ;H

/ ]/ ... .. — . 4_ ^ | /

mj — . — — — f, S\

NPI2CI

110 4 c LJ. CJ

QO _ — 1 1 30 — — —

Qi11 k"" i*~ "" ~""™ ^r X- •W ^rv-ptV

JU

oc 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3


64

AEDC-TR-74-75

SYM CONFIG STORE CM CC g 21 PYL0NS+370TPNKS 48311 33C O 23 ERSH 49683 33C

H=20.000

t ' I

! 30 ' ~— i !

It ■ > ii

X\J / /1

3U ~♦""

L J ^r 4t> — —|— —

/ M /

HPttCI (tt^/ ., * „

i / / 4c "~ "" —jjfi 51 f A I {[

D\ /

JÖ "~ ~" ~\T~

t1m*C/ S' _ Ä — "" *4 JHlh ^. — -<)- "rl

<> "^

3U ~

i OC I— Ö.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3


65

AEDC-TR-74-75

STH CONFIG STORE GW CG □ 21 PYLONS*370TANKS 48311 33C O 23 ERSH 49683 33C

H=30.000

Cft — — —1 JÖ ■ ■

cu — — S4 ^ i ■

! 1 ^ in !■ i -> ^ ' 3U —r- ^ i

.. _ _ ./irl/r« 1 1 1 ,^^ \ i !

IIC 1 rfl^ .rf^^ 4D -"J-~

/ET t MPIXT.1 /ir i

nL*f ' no .., _.. _i_ i/jjfi' i 4ci "

// I JcT

oo _ __ £ 3 ]

ON .C.J. J4 JL?t'\

—•""* t\~*-- \l- — ~~

an _ JU 1 i : I

oc - L. 1 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3


66

AEDC-TR-74-76

STH CONFIG STORE CM CO O 21 PYLONS«370TflNKS 4831t 33C O 23 ERSH 49683 33C

c»

H«10.000

°I^-==5R5> I " n nnu - - ... '^fel ,

k -u.uuo ■"■ ^^:L

^*sK ^S^||.

i

0.004

0

-0.004

-0.008 m -0.012

-0.016

-0.020

H-SEfi LEVEL

-0.024

«P—=lBSi « §0 sfv t^ 5^

**** %»- XI

■ t 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

a. H = Sea level and 10,000 Figure 22. The effect of the Stubby HOBOS store on the slope

of the pitching-moment coefficient versus angle-of-attack curve at trim.

67

AEDC-TR-74-75

STH CONFIG STORE GH CG 0 21 PTL0NS*370TflNKS 48311 33C O 23 ERSH 49683 33C

H=30.000

n,H" *"s N S. i

\ n nnn N -D.ÜU4 i h S ft -U.UUO ;* -* 1

n m "> —— w^ y s >* i

1

-U.Ueu

H=20.000 0.004

-0.004

c». -0.008

-0.012

-0.016

-0.020

-0.024

j k JB

- W-K 5EEL 5K £s^ v2^

^^1

i 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4


68

AEDC TR-74-75

CL.

SYH □ G

0.10

0.09

0.08

0.07

0.06

0.05

0.09

C^ 0.08

0.07

0.06

0.05

0.09

CONFIG STORE GH CG 21 PYL0NS*370TRNKS 48311 33C 23 ERSH 49683 33C

H=30.000

H=20.000

1 f-, OU ny*-i J*4_ J CM 11 i *■" ^^_

"TtTTll— I I 1 I ! 1 Mill

H=10

H=SEA LEVEL 0.05

0.09

C,. 0.08

0.07

0.06

0.05 6 7 8 9 10 11 12 13 14xl0->

Figure 23. The effect of the Stubby HOBOS store on the lift-curve slope at trim.

69

AEDC-TR-74-75

STH CONFIG STORE GH CG Q 21 PTL0NS*370TANKS 48311 33C O 23 ERSH 49683 33C

1 i« 5ER LEVEL

o y

8 -

7

6 ■

w tr 5

U

3 i

2 -o-

i "Q-

l

0 j

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

a. H = Sea level Figure 24. The effect of the Stubby HOBOS store on trim wing angle of attack.

70

AEDC-TR-74-75

SYM CONFIG STORE GW CG D 21 PYLONS*370TRNKS U8311 33C O 23 ERSH 49683 33C

i n 1 4s 10.000

1U

9

8 1

7

6

*w tr 5

>1

3 1

2 cEnvuls, *Q-

i 1

n 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

M, '00

b. H = 10.000 Figure 24. Continued.

71

AEDC-TR-74-75

SYM CONFIG STORE GW CG B 21 PYL0NS*370TfiNK5 48311 33C O 23 ERSH 119683 33C

1 i* ; 20.000

9 \

8

7

6

w tr 5

U

3

2 ""13-

i

i i

l i

n | 1 1 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4


72

STM CONFIG STORE GH CG

D 21 PYL0NS*370TflNKS 48311 33C O 23 ERSH 49683 33C

AEDC-TR-74-75

1 i= 30,000

Q y

Q 8

7

6 aw tr

5

4 ^ö

HX

3 tk

2 ■t J

i

■

1

n 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

n 'oc


73

AEDC-TR-74-75

SYH CONFIC STORE GH CC Q 21 PTL0NS*370TRNKS 1831i 33C O 24 TCTV 50811 33C

-10

-8

-6 Sir

0

-8

-6 Sir

-11

-2

0

-8

Sir

-2

0

-8

-6 Sir

-U

-2

0

H«30.000

fflft A J»

iBS?*:::^ ,„^^" g-' ±:

H=20.000

^y i»k

H= 10 .01

H=SEA LEVEL

ps===*MNSp-^fc = s^1

6 7 8 9 10 11 12 13 14x10-«

Figure 25. The effect of the TCTV store on trim stabilster angle.

74

AEDC-TR-74-75

SYN CONFIG STORE GH CG

□ 21 PYL0MS*370TflNK5 «18311 33C O 24 TCTV 50811 33C

H=SEfl LEVEL ot: -- - ' ' : "- '

J I

| 30 [ "" "~

'

34 ""'

j

en , _ , . ^i

JU I i

4b ■■' r"!~ NPtXC!

If] £

in . f[/\ Hd !

i

P n\ i / 1

QP i l\ r-W i JO /© r*f i

ll/l i

L(j-Krip 341 r — — Ä

^J ^faO^l

1 i

*>n JU

oc - - .

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3-

a. H = Sea level Figure 26. The effect of the TCTV store on neutral-point location.

75

AEDC-TR-74-75

STM CONFIG STORE CM CG B 2\ PYL0NS*370TRNKS «8311 33C O 24 TCTV 50811 33C

H=10.000 0£ ----------

30 "' ~J "" ""*""

" ..... ,,,

ClI _ , , I , ,_,,_ _ .., __.___-_ Jl J4 ~ " 1 1^

/l^) A ^*

cn ■ ! j /r ! i ' ' A f j J /\ i i / 1

i ! 1 ' ' t' 1 t f | i ' 4G ! ; | : i | ^' j i

NPrari j j /if

' ^rk W dn /y - illy/ !

Jo '"f" ■■" /f^-d^ljjy [" — "" []/ v/ 1

»Ejinidajff j i L1 1 A i 1 1 :

JU -1 ■ r ■ I ' ' " i 1

oc i ; -J 1— 0.6 0.7 0.8 0.9 1.0

Moc

1.1 1.2 1.3


76

AEDC-TR-74-75

STM G o

CONFIG STORE CW CG 21 PYL0NS+370TANKS U8311 33C 24 TCTV 50811 33C

H=20.000 D<£ -]

3D " ~ ~ — ~" "~

.. t>4 ~ ~" ""*""

T | /f'v0 i

sn . I j£s 3U — —♦— j I AY

f\ ~} IIC i i 11 413 1

/ ' NPIXC1 Jj

ft HO , J, 4c ^^ PY

3 ty '" 11 \ /J LA j f'

AW Jo " ~ ~ '■ | f "]]/ ^r t — — —

I i^-f f1 i»

OM i i_ — — -""" "" , , / vd-» J41 r ^ xy m*ir ^.~*-"J'

(f

o\J —

OC __ —

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3


77

AEDC-TR-74-75

SYM CONFIG STORE CW CG □ 21 PYLGNS+370TRNKS «18311 33C O 24 TCTV 50811 33C

62

58

54

50

46 NPCXC)

42

38

34

30

H*30.000

26

1

r| I /vO

' j^ ■ ^r

\J& ■ ss^

yf r 4r .f

f fXl/

JTJf tHD

W^ // 1 if 1 / /

/ ' .// 1 /Tj

jÄilJo .* ■""'*"J*^

I F "" «^ x

"^ \r' L L

0.6 0.7 0.8 0.9 1.0 l.l 1.2 1.3

Moc

d. H = 30.000 Figure 26. Concluded.

78

AEDC-TR-74-75

STH CONFIG STORE GH CG G 21 PYLON5*370TRNKS 46311 33C O 21 TCTV 50811 33C

0.001 H MO. 000

1 1

Oi 1 i

ui J- -1 W -A

-0.001 i L f k r *Si

-0.008 i Lfi

F

-0.012 i

-0.016 !

-0.020 " i j

-0.021 H=SEfi LEV

0.001

0

-0.001

-0.008

-0.012

-0.016

-0.020

-0.021 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.1

a. H - Sea level and 10,000 Figure 27. The effect of the TCTV store on the slope of the pitching-


fc

79

AEDC-TR-74-75

SYM CONFIG STORE GM CG 0 21 PYLONS*370TRNKS «18311 33C O 24 TCTV 50811 33C

0.004

0

•0.004

H»30.000

c» .0.008

-0.012

-0.016

-0.020

-0.024

0.004

-0.004

b. ■■•« ->. M L

ks r N i I X

% >t i S y k

> i > 1

i i

H »2( ).C 00

c«. -0.008

-0.012

-0.016

-0.020

-0.024

i »

X—

A fcW yrj cy ^v

-1 1

.

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4


80

AEDC-TR-74-75

STM □ 0

0.10

0.09

r 0.08

0.07

0.06

0.05

0.09

C,.. 0-08

0.07

0.06

0.05

0.09

^ 0.08

0.07

0.06

0.05

0.09

0.08

0.07

0.06

0.05

-L«

CONFIG STORE GW CG 21 PYL0NS+370TANKS «48311 33C 21 TCTV 50811 33C

H=30.000

H=20.000

i i

ft fi>

fe s»

J L =~: =^ S i r y i

h 1= 0 .01

H=SER LEVEL

6 7 8 9 10 11 12 13 lUxlO"1

M. oc

Figure 28. The effect of the TCTV store on the lift-curve slope at trim.

81

AEDC TR-74-75

SYN CONFIG STORE GH CG 0 21 PYL0NS*370TANKS 48311 33C 0 24 TCTV 50811 33C

i n 1 i= 5Efl LEVEL

Q 3

Q •

o

7

6 aw tr

5

U

3'

2

nffl j

1 ~Q-

1

n 0.6 0.7 0.8 0.9 1.0 1.1

a. H = Sea level

1.2 1.3 l.U

Figure 29. The effect of the TCTV store on the trim wing angle of attack.

82

AEDC-TR-74-75

STH CONFIG STORE GW CG □ 21 PYLONS*370TANKS 48311 33C O 2M TCTV 50811 33C

i n 1 1* l0.000

9

8 i

7 i

6

1 1 1

w tr

5j L '

4 N ^ X

^

3 \

^sf >q k 2

■4 s ItCL, *l k&

13- (

)■—

—— -—~ h t

i

i l

n O.S 0.7 0.8 0.9 1.0 1.1 1.2 1.3 l.U

Hoc


83

AEDC-TR-74-75

STM CONFIG STORE GH CG B 21 PYL0NS*370TMKS 48311 33C O 24 TCTV 50811 33C

i n H= , 20.000

1U

Q y

8 1 1

-7, ! 1

i

1 < L 6 NS V

i \ !

^ ^

w tr 5

\ i

i

U |

3 ^^^

baf vßv Npi

2 ■^■3 >

■ I

0 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4


84

AEDC-TR-74-75

SYM CONFIG STORE GH CG D 21 PTLONS+370TANKS U6311 33C O 24 TCTV 50811 33C

10 1 H= 30.000

Q y

Q O

t 1

e O

*w tr c ^\i b

m\

■I T^ 4

CD XÖS

3 & *^r i k

o

n J

C

1 1

n 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

d. H ■ 30,000 Figure 29. Concluded.

85

AEDC-TR-74-75

STM CONFIG STORE GH CC □ 21 PYLONS»370TBNKS 48311 33C O 25 PF MOO HPN P 53511 33C A 26 PF MOD HPN UP 53611 33C

H«30.000 -IU

-B o

-6 Sir

-1«

o ^-"'

H

-2

0 H=20 .01

-8

-6 Sir

-2

0

-8

-6 Sir

-2

o -8

-6 »Sir

-4

-2

0

H=l0.000

& ^ 1

H= SE 0 1

J g L w ^ s

H D r 0 o tk ,1 £ ? !*! i_ 11= -1 H H r1

8 9 10 11 12 13 111x10-"

Figure 30. The effect of the PF Modular Weapons stores on trim stabilator angle.

86

AEDC-TR-74-75

SYM CONFIG STORE GM CG

Q 21 PYL0NS*370TANKS H831I 33C O 25 PF MOD WPN P 53511 33C A 26 PF MOD WPN UP 53611 33C

H*SEfi LEVEL

oö - — — ——

34 — — —

i i 1

/ ou ~~p ~" yfy ^A

/ / s'As _ 2Sz£ 40 "" ~* ""T" / tAs I

NPIWI

!•-) 4l ,..,,! 4fi — — —

i m | / 30 "" "" """" / f^k 1 /,

JT"1 * »

Jmr-Tl1- -—•■'" ■ '■ ■

on oU

oc ____ — ___ — _ — |

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 Ice

a. H = Sea level Figure 31. The effect of the PF Modular Weapons stores on neutral-

point location.

87

AEDC-TR-74-75

SYH CONFIG STORE GH CG D 21 PYLONS*370TPNKS 48311 33C O 25 PF MOO WPN P 53511 33C A 26 PF MOD WPN UP 53611 33C

H=10.000 on

Cfl DO r- -

till — U l i)4 i 1 ^

1 l> > tin X s* \/ JU { X y /

i ,(\XV y'V* I mj _ ——*— - i^/\ i

NPfifCI { i m<-\ 1

; 1 ■ i Lf\ i s 115 I ; ' r^7 ' 4fc ; 1 >**i fii/i

0 A /y XiwJL

QQ ra/1 ' n DO ~ —T- - 1 X i\ T7 i

,. _, =t r- -&\- jrv&j 1~ 34lfc==r r /■ i-W —| —|—;"

<>= =pbb^:a^«£ -i ! j j- 1

an 1 1 1 JU

*3C — J. 0.6 0.7 0.8 0.9 1.0 1.1

Hoc

1.2 1.3


88

AEDC-TR-74-75

STM CONFIG STORE GW CG Q 21 PYL0NS*370TANKS 48311 33C O 25 PF MOD WPN P 53511 33C A 26 PF MOO WPN UP 53611 33C

H*20.000 X)d 1 -T- ■■■ r , —f ■' r T— "TT

■ \ \

■ : i

CO 1 1 i 1

JO i ! i ! ! ! 1 i T .

tu 1 i ' L 54. | i f\ J^ |) iky

m i , ., _. i • i A sC/\ JU : | . , i / '/ > i *

! ! ' , ; | j ! ! i

j ! ! i ■ i

UC i IT j|

X' i

HO i jfii wpr/ci \jff

i\/\i tlO _......., . i Id/ 4c jFh fif\

! /0 :\i /; -1

OO . _1_ V/.iÄPV ' JO Wit &*>( 1

1 i

AY Jf n !

QM f » -■— *" 1 J4I}- —

' ■—r * 1"*

an , JU i

( 1 • r

*e ~T"_ " X- 1 i 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3


89

AEDC-TB-74-75

SYM CONFIG STORE CM CG D 21 PYL0NS+370TPNKS «18311 33C G 25 PF MOD WPN P 53511 33C A 26 PF MOD WPN UP 53611 33C

H=30.000 D«: ""1 1 CO 1 JO

!

ClI , i t>4 ^^ _/I

^n ! 1 ^£ 0**^ls t JU T~" •<\f ' ... 1

.... J £ M .^^

\ rf/lf1

lie .__!_ i w /; _^^

4b fi3

NP ran \\X/

in i I J 42

7\ &i 1 j\ 7 j I

1 1 [Xfj^ 1 !

"JO - ■ J / m ^^ / Ab. / / u\J

□' 11 T Qll r /(( 34 ^^ j

^ // tsA^f

"~ -*^ ^ >-»<J7 on - "^ 30 ^2 1

<r 7 7

ocikll—Mill _..].. 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3

M, oc


90

AEDC-TR-74-75

SYH CONFIG STORE CM CC Q 21 PTL0NS«370TANKS "48311 33C O 25 PF MOO WPN P 53511 33C A 26 PF MOD WPN UP 53611 33C

H=10.000

[H L

E k ft

\ s I» i s V s s ^ \-

i i

i H=SEA LE

0.004

-0.004

•0.008 m -0.012

-0.016

-0.020

-0.024

0.004

-0.004

-0.008

-0.012

-0.016

-0.020

-0.024 ■0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

a. H - Sea level and 10,000 Figure 32. The effect of the PF Modular Weapons stores on the

slope of the pitching-moment coefficient versus angle- of-attack curve at trim.

—_ 1 ^s^i

91

AEDC-TR-74-75

STH CONFIG STORE GN CG Q 21 PYL0NS*370TANKS 46311 33C 0 25 PF HOD HPN P 53511 33C A 26 PF MOO HPN UP 53611 33C

O.OOI

0

-O.OOil

-0.008

-0.012

-0.016

-0.020

-0.021

0.004

-0.001

H=30.000

ils «^- *"*■<: =3 P s 1 w\ —t h \

V i w *«| i

$ *u 's *N

'S ks ^3 &

I 1 1

c«. -0.008

-0.012

-0.016

-0.020

-0.021

H=20.000

A

Ü ra Gr

Q.

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4


92

AEDC-TR-74-75

STM

O

0.10

0.09

r 0.08

0.07

0.06

0.05

0.09

CL. 0.08

0.07

0.06

0.05

0.09

0.08

0.07

0.06

0.05

0.09

0.08

0.07

0.06

0.05

*L«

-L«

CONFIG STORE CW CC 21 PYLONS*370TANKS 48311 33C 25 PF MOO WPN P 53511 33C 26 PF MOO WPN UP 53611 33C

H=30.000

, & 'I ^Sf ^

i^rfe0^?^^, <W* r*' i 3?^ . T .

Y7 ! i r - x i ± H=20.000

A !

h r n fe J J «* ,

\p 0* -*= H Hi f « ^ 1

H=10.000

H=SEA LEVEL

7 8 9 10 11 12 13 14x10"» M. 'CC

Figure 33. The effect of the PF Modular Weapons stores on the lift-curve slope at trim.

93

AEDC-TR-74-75

SYM CONFIG STORE GW CG

D 21 PYLONS*370TflNKS 48311 33C O 25 PF MOD WPN P 53511 33C A 26 PF MOD WPN UP 53611 33C

i n 1 1= {

SEA LEVEL 1U

Q 3

8

7

6

"w tr 5

\ s 3

1 ^ s s

^s s.

2 sS

is, •s *3 iQt iff =ß= =*t U^ ■—. *"■«

1 'uj -O- C I— — — "^ 1

0 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 l.U

K 'oc

a. H = Sea level Figure 34. The effect of the PF Modular Weapons stores on the trim

wing angle of attack.

94

AEDC-TR-74-75

SYM

□ O

CONFIG STORE GW CG 21 PYLONS*370TANKS «831! 33C 25 PF MOD WPN P 53511 33C 26 PF MOO WPN UP 53611 33C

1 ■1= 10.000

Q

i

9

8

i

i

7

6

w tr 5*

U

3

2 &*& =ft= saf U.

• 1

0 |

0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 l.»4

95

AEDC-TR-74-75

SYM

O

CONFIG STORE GW CG 21 PYL0NS*370TRNKS 48311 33C 25 PF MOD WPN P 53511 33C 26 PF MOD WPN UP 53611 33C

\ 1= i 20.000

1 9

1

8 i

7 ■

6 r V

i

"w tr 5

w ii

i 4

Q 3 \ «Ü! tvfT

2

1 J * ^TD-

i^$ i I

i 1 1 0

< i

0.6 0.7 0.8 0.9 1.0 1.1 Mcc


1.2 1.3 l.U

96

AEDC-TR-74-75

SYM □ o

CONFIG STORE CM CG 21 PYL0NS*370TRNKS »18311 33C 25 PF MOD WPN P 53511 33C 26 PF MOD WPN UP 53611 33C

1 is 30.000

9

8

7

6 ,

w tr 5

4 l?| JEL

3 tk

2

-"t l—

i l

n 1 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4


97

AEDC-TR-74-75

STM CONFIG STORE CM CC □ 21 PTL0N5*370TRNKS «8311 33C O 29 ONEHflT RPV 9(311 33C

-10

-8

-6 Sir

-«I

0

-8

-6 Sir

-2

0

-8

-6 Sir

-y

-2

0

-8

-6 Sir

-4

-2

0

H*30.000

r*

H=20.000

J e & 2 y 1— u r •^ NJ u

H= IG .01

i ■L*. _r" ÜSfes^^i l^-^aF,H

H=SEA LEVEL

£\ fcl

p J 1

6 7 8 9 10 11 12 13 14x10-1

Figure 35. The effect of the Oneway RPV store on trim stabilator angle.

98

AEDC-TR-74-75

SYM CONFIG STORE CM CC

Q 21 PYL0NS+370TANKS U831! 33C O 29 ONEWRY RPV 54311 33C

H*SEA LEVEL D£

bB "- ~ "" — —

D4 "~ ""*"" "~ " J/" 1

cn » _ _ f

all

. y» X

40 T~ \~ — «eci *

HC _a: L ^ xiji . SLAZZ Z 3v +— So 1— ~ — r /

—A ~f3E -,**■• -3f

on,, |fc3E - X £ £ afe3rjl

^n<t =<y==i^ 3\Jy*-

OC ___1__ — 1 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3

Hoc

a. H = Sea level Figure 36. The effect of the Oneway RPV store on neutral-point location.

99

AEDC-TR-74-75

STH CONFIG STORE GW CG □ 2\ PTL0NS+370TRNKS 48311 33C O 29 ONEWAY RPV 54311 33C

H=l0.000

30 ""*" ■

QU — J4

OU

MC 40

NPIXC) t 1 / !>

! 4c

' _./Tn C 171 ^f f

1 \ /' 3P 1 Wl Jo 1' U'

i r) (jr*^ jt^X '/I j

OH It —'** ffl 34lf= /I /[

O an

-{)--**- j JU I i

j

DC — in: 1 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3


100

AEDC TR-74-75

SYH CONFIG STORE GH CG □ 21 PYLONS*370TANKS 48311 33C © 29 ONEWAY RPV 54311 33C

H=20.000 D* —q ; p

So ""*~"" — """ 1

C1I 1 1

34 "~ 1 t 1

i i 1

OU ' i

>f\ . >

\r ma — "~ | 1 \j

NP IXC) i AH/

L /r7 i

He ' ""1— " "

/' \ y p i I QQ ■ / JKX* JO )' r\ / j \

•u „. -4-" *" «J4l 1"

nn -rf" jUtyj^-^ \

oc 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3

Mce


101

AEDC-TR-74-75

SYM □

CONFIG STORE CM 21 PYL0NS+370TRNKS «8311 29 ONEWAY RBV 54311

CG

33C 33C

H»30.000

i . t_j: T Ji i. CO

' 1 ) 1 i 1 1 JU ! ! i i j i

' "i ^ 4 ! i i i

i

i • [ 1 i i i i ■4nt, J i 11 1 ' 1 ■ 1 J i J/

1 i 1 ■ I • ! ■ 1 ' I */l . : 1 ' 1 ' i ' I

CLC\ 1 i ' 1 ! ' : ' i. a^ril JU j | i ! yy 1 1

* i 1 ! ! " ijLY^/r'i i i

i ! \/r\l^ "T

■f" ! 1 l

HG j | i ! \ \ & ■: ! 1 1 i NPI2C1 , i|; i 11 i r*; i i

1 ! 1 i ■ PI \s i ■ 1 i /7*f?f • J ■ : i ll*> .. i rtf ' i / 1 i : i 42 , . [ V1 ! ;/ ■ j [ 1 1

/: I A S i ■ '. 1

! i /GXJ P ! 1 1

1TI —In ! i tiMb1! ! i JO — t" 1 i / / 1 ' | '

■ ' / 1 i ' Im!?'! i

-m ■/" 1 / 1 ! J4 j r i /

!/ ij—pL--" ii/

JU ' j>" ■ l 1

]s\ i , 1

jS j oc (kl — ! i . ! 1

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 'oc


102

AEDC-TR-74-75

STM CONFIG STORE CM CO B 21 PYLONS*3707ANKS 48311 33C 0 29 ONEHRT RPV 54311 33C

0.004

0

-0.004

H=10.000

c». -0.008

-0.012

-0.016

-0.020

-0.024

0.004

0

-0.004

>- MM> 1^" —( H H I *-i H N \ i o ft

k r v_, H --< ^

\ s i ^ \ , N

N k *i i

H=SEfl LEV

Cm- -0.008

< h ■<>-< n \,

l\- HM s X i

\) i \ *v. 11 w x V a

% s ^ s S v.

^ I JI t -0.012

-0.016

-0.020

-0.024 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

a. H = Sea level and 10,000 Figure 37. The effect of the Oneway RPV store on the slope of the pitching-


103

AEDC TR-74-75

STM COfflG STORE CM CG 0 21 PTL0NS*370TPNKS 48311 33C

29 ONEHflY RPV 54311 3X

0.004

-0.004

H=30.000

C^ -0.008

-0.012

-0.016

-0.020

-0.024

0.004

,J^

'»- —«S 5üH- 5C-

te^ SöL 5=*t C=^

4^ ^ss;:- ^n

i 1 i

-0.004

Cm- -0.008

-0.012

-0.016

-0.020

-0.024

H=20.000

>- -—1 —1 >-< K

Hi \* N V in y. ft h fey Ö u 1 \

'v s I <\J S

s N i -1 1

0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

b. H = 20,000 and 30.000 Figure 37. Concluded.

104

AEDC-TR-74-75

SYM

G O

0.10

0.09

r 0.08

0.07

0.06

0.05

0.09

^ 0-08

0.07

0.06

0.05

0.09

0.07

0.06

0.05

0.09

^ 0.08

0.07

0.06

0.05

CONFIG STORE GH CG

21 PYL0NS*370TANKS »18311 33C 29 ONEWAY RPV 5M311 33C

H*30,000

— -1- |

I | I

t5 Q'j i

— HO- i \

— ■^\

•— ■j&k J-~ — -!- -p- —

fT "? i ■ T—

i

, i i

H=20.000

H=10.000 1 — 1

F\ I i

.5 nl* J *t

1 I

i

H=5Efl LEVEL

Gu.

SH^"" .TES zj>^S~

1

6 7 8 9 10 11 12 13 14x10-« M, 'oc

Figure 38. The effect of the Oneway RPV store on the lift- curve slope at trim.

105

AEDC-TR-74-75

STM CONFIG STORE CH CG B 21 PYL0NS*370TflNKS 48311 33C O 29 ONEWAY RPV 54311 33C

10 1 H= 5Efl LEVEL

9 i

8

7

6

w tr 5

4<

3

2 nQu JSt

i "Q-

l

0 0.6 0.7 0.6 0.9 1.0 1.1 1.2 1.3 1.4

a. H = Sea level Figure 39. The effect of the Oneway RPV store on the trim wing angle of attack.

106

AEDC-TR-74-75

SYM CONFIG STORE CM CG B 21 PYL0NS*370TRNKS 48311 33C 0 29 ONEWAY RPV 54311 33C

i n 1 H= 10.000

1U

9

8

7

6

5

4

3

2 TQL y0- -0-.

liL vOs, *Q-

* 1

n 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 l.U


107

AEDC TR-74-75

STM CONFIG STORE CN CC □ 21 PYLONS*370TRNKS M8311 33C O 29 ONEWRY RPV 54311 33C

1 -1* ■ 20.000 1U

Q y

8

< V A v

6 \ \

L 1

w tr 5

4

3 l TLM^^

2 ^G-

i

1

0 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 l.U

M, 'CC


108

AEDC-TR-74-75

STM CONFIG STORE GW CG Q 21 PYLONS*370TflNKS ¥.8311 33C 0 29 ONEWRT RPV 51311 33C

1 1= 30. D00

9

Q 0

T 1

c b

aw tr 5

\ i\

\i \ i t i

■I

X XL 1 1 •**•!- 4

GL- ~X\ ■u* ^< k s

o tV.

J *t >

o c

1 1

0 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4


109

AEDC-TR-74-75

STH CONFIG STORE CH CG □ 21 PYL0NS*37OTRNKS «8311 33C O 30 ERV 53311 33C

H=30.000 -IU

-8

-6 Y>

v> ■Q.

\-

n

-8

-6 Sir

-2

H=20.000

i£!sb==:

HFIO.000 -o

-6 Sir

-•*

-2

H=SEft LEVEL

-6 Sir

-4

-2

0 6 7 8 9 10 11 12 13 lUxlO-i

Figure 40. The effect of the ERV store on trim stabilator angle.

i\

110

AEDC-TR-74-75

SYM CONFIG STORE GH CG

D 21 PYL0NS+370TANKS 48311 33C O 30 ERV 53311 33C

H=SEfi LEVEL Ü£ ---------

| ca _ _ __ _ _ IjQ _ |__ _

i ■ 1 1

■ :

Cll — __—~— — i 1 !

34 ^T^ i i

t i XXI

i i i> /l 1 3U — "1

1 iX n ! i i

i i ... •. j

4o T 1— 1 ! / x 1—i

NPßCI V\J >' *

1 r / _i_ 1 ' /' 4c ~~| JH ii/l i

1 I Y \J f i

i 1 i ■1

Jo ™*~

t- r-JW J' 1/ T

an ri.-*« —:""^i! -r-yT •/ j4lr —— " — m

an _ JU +-

oc : __:£__: 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3

a. H = Sea level Figure 41. The effect of the ERV store on neutral-point location.

I!

AEDC-TR-74-75

STM CONFIG STORE GH CG □ 21 PYL0NS+370TRNKS 48311 33C 0 30 ERV 53311 33C

62

58

54

50

46 NPC/XI

42

38

34

30

HM0.000

26

,

_ .. _., ..... _ j_ (_..

J 1 ^ JSS

J^tf / \j

f s y j' f y

f J {i / ' f /

tv ty //1

J. dy GfW ^ / \ y' 7 t V /

/ M 11 O^*

-U--"' / It --^ _

<*=-« -,*-**' -« o-=*^

x inn: 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3


112

AEDC-TR-74-76

SYM CONFIG STORE GW CC Q 21 PYLONS*370TRNKS U8311 33C 0 30 ERV 53311 33C

H=20.000

DO — — — —+— — —

, _ J| 34 — —

fZ ^S- X- /. z Cft _____ ____ _ I . /L2_ ou :^^^

/ / -/*■+- -J2-

MC __ 4X- 40 - J%- NP r/X) - M.4 «/ t ZL—L

PHD 4J1 Z^C 4-( / JL I \ -

^ft -U^2 31/- ^5^--

***¥+ 341 J- — * - , _

_--(>-w/

JU

_ __i 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3


113

AEDC-TR.74-75

SYH CONFIG STORE GM CG Q 21 PYL0NS*370TRNKS «J8311 33C 0 30 ERV 53311 33C

62

58

54

50

46 NPKCI

42

38

34

30

H=30.000

26

1— . \

—i—i—i—I ? !

J! ! .^r^^r

• ■

1 H-/-Kjp^ -1- i—H JÜ-1—1 1— — L-J-t ^-• ) »J J— T-^Jf ■ - ■ i | — 1 — — -j- 1 ; i —,—

1 L~\— i /

/ '/ -+- j

~~~ ^Jf Jn- i

IP=F"~! A-^T~- _l

:::;^=:=:::::

,fe=ffi8=:: 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3


114

AEDC-TR-74-75

STM CONFIG STORE CM CC G 21 PYLONS*370TRNKS M8311 33C O 30 ERV 53311 33C

0.004

0

-0.00(1

-0.008 HP

-0.012

-0.016

-0.020

-0.024

0.004

o

-0.004

-0.008

-0.012

-0.016

-0.020

H=l0.000

Y- ~ ■-^ —< M H 1 —1 M K, X t o Ä

h r s» s i N k i

N < ^

Tl

H=SEfl LE

-0.024

>- M H \* \- —1 In s, ,A i y & V r u ■HI • w v. »<

^ bJ *s S s, X t

1 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

a. H = Sea level and 10,000 Figure 42. The effect of the ERV store on the slope of the pitching-


115

AEDC-TR-74-75

SYM CONFIG STORE CM CC D 21 PYLONS+370TRNKS 48311 33C 0 30 ERV 53311 33C

c*.

0.Q04

0

-0.004

0.008

-0.012

-0.016

-0.020

-0.024

0.004

H»30.000

Q

Q

*& 's S s .-< >— — ^ w h n

H=20.000

-0.024 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4


116

AEDC TR-74-75

SYM □ O

0.10

0.09

r 0.08 k«

0.07

0.06

0.05

0.09

CL. 0.08

0.07

0.06

0.05

0.09

C,. 0.08

0.07

0.06

0.05

0.09

km 0.08

0.07

0.06

0.05

CONFIG STORE GW CG 21 PYL0NS+370TPNKS 48311 33C 30 ERV 53311 33C

H=30.000 ^

: —

i rt i

i | 1 u i

— "1 ' _i_ -4- 1"*'

■ i . 1 i 1 i i

i 1 H=20.000

i ;

©I i 1 t

1J ^^ i

J i

00 4 ^J 1 i 1~ 1 i

i i

i 1 1 j

H= 10 .01

— ■»—. — — —— _

H=SEfl LEVEL 1 1

» j JB

y ■** -* ~-, S i

6 7 8 9 10 11 12 13 14x10-» K oc

Figure 43. The effect of the ERV store on the lift-curve slope at trim.

117

AEDC-TR-74-75

STM CONFIG STORE CM CG D 21 PYL0NS*370TRNKS 48311 33C © 30 ERV 53311 33C

i H= « 5EA LEVEL

o y

Q Ö

7

6 aw tr

5

ii. -

4 (

3

2 TOU J3T ^D—

i ^Q-

l i

0 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 l.U

a. H = Sea level Figure 44. The effect of the ERV store on the trim wing angle of attack.

18

AEDC-TR-74-75

STM CONFIG STORE GH CG B 21 PYL0NS*370TRNKS 48311 33C O 30 ERV 53311 33C

i n 1 ■fs 10.000

IU

o y

8

7

6

5

4

3

2 TV v®" -©*

tiL yO». "■O-

i 1

n 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

K 'oc


119

AEDC-TR-74-75

SYH CONFIG STORE GH CG D 21 PYL0N5*370TRNKS «8311 33C O 30 ERV 53311 33C

1 hi» 20.000

Q ä

8

( v ,\ K

6 \ \

, v aw tr

5

U

3 y^s

^wJ%

2 TD-

~J >~~

• I

n 0.6 0.7 O.B 0.9 1.0 1.1 1.2 1.3 1.4

K oc


120

AEDC-TR-74-75

SYH CONFIG STORE GH CG □ 21 PYLONS*370TRNKS M8311 33C O 30 ERV 53311 33C

10 1 i= 30.000

Q y

a O

t 1

e D

"w tr \ i

3 |i 1 %

M el

4 ^ K V

3 eV.

o *"*T I

d

\ 1

n 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4


121

AEDC-TR-74-75

- 5 CONFIG 22 (SOM)

ANP

- I

O

I

»

CL-0.2

85»-0.6 dag

ANP

CONFIG 23 (ERSH)

f\ 1 n9

J 1

0 [

C^ —r>

ANP

CONFIG 24 (TCTV)

0.5 0.7 0.9 II 1,3

Figure 45. Incremental change in neutral-point location due to various external stores at a lift coefficient of 0.2.

122

AEDC TR-74-75

ANP

- 7

-5

-3

— I

0

I

O C0NFI6 25 PHILCO FORD MOD WEAPONS POWERED

G CONFIG 26 PHILCÖ FORD MOO WEAPONS UNPOWERED

fi t if

-t-i 4 Sz \J

C^O.2

8^— aedtg

-8 CONFIG 27 NARC CLASS IE

ANP Q

P

/ H

f ">—' u f

Q

\ /

\ . 1 \ J \ Y

0.9 0.7 0.9 I.I 1.3

Figure 45. Continued.

123

AEDC-TR-74-75

CONFIG 2B NARC CLASS XX

ANP

-■8

-6

-4

-2

1 1 1 1 —1 1 1 1

pj

i JO s

j£ b^

CL-0.2

8^-0.6 d«g

ANP -7

-5

CONFIG 29 ONEWAY RPV

P

f A \ c 3—■ ——* 1

\ JO

, /

kr V 0.5 0.7 0.9 1.3

Figure 45. Continued.

124

AEDC-TR-74-75

O CONFIG 30 ERV

ANP

- 2

e 4- \

y- o-o 1

k V-1

i 0.5 0.7 0.9

CL- 0.2

S^>-0.6 dtg

I.I 1.3

Figure 45. Concluded.

125

AEDC-TR-74-7S

CONFIG STORE

0 22 SOM

D 23 ERSH

0 24 TCTV

V 29 PF MOO WPNS P

u 26 PF MOO WPNS UP

0 27 NARC MOO WPNS CLS m A 28 NARC MOD WPNS CLS n 0 29 RPV o 30 ERV

ANP.

10

- e

UNFINNEO STORES ( REF. 2)

-FINNED STORES (REF. 2)

Mo «0.85

CL»0.2

s. 0.6

12 14

AF(FT2)

a. Wing-mounted store frontal area correlation

O PREDICTIONS (REF.3)

a WIND TUNNEL RESULTS C0NFI6 23 ERSH

ANP, tr

-to

- 8

- 6

- 4

- 2

4 2

6W «49,683 H> 10,000

1—D—' J /V—^

^ Q

3 0-f 1 n / ,

0.6 0.7 0.8 0.9 1.0 I.I 1.2 1.3 M.

b. Generalized prediction technique of Ref. 3 {configuration 23) Figure 46. Comparison of measured neutral-point shifts with results

from existing prediction techniques.

126

AEDC-TR-74-75

ANP. ■10

- e

- 6

- 4

- 2

O PREDICTIONS (REF. 3)

D WIND TUNNEL RESULTS

H« 10,000

< CONFIG 24 TCTV

GW-50,811

n 1—1 >-o-( Sv< •\ . ^S ?— -^r~ JOOO °N

0.6 0.7 0.8 0.9 1.0 I.I 1.2 1.3 Um

c. Generalized prediction technique of Ref. 3 (configuration 24)

CONFIG 30 ERV -10

ANP„ - 8

- 6

- 4

-2

0.6 0.7 0.8 0.9 1.0 I.I 1.2 1.3

d. Generalized prediction technique of Ref. 3 (configuration 30) Figure 46. Concluded.

QW« 53,311

A

i

^r y >— —-p

^ ^4

127

AEDC-TR-74-75

5YM CONFIG STORE GH CG □ 21 PYL0NS*370TfiNKS 48311 33C O 22 SOM 52311 33C

H=SEA LEVEL u. \c

nti U. 1 I

0.10

0.09

0.08

0.07 cDtrim

0.06

G

d

0.05 P f J

0.01 r < f i 0.03 —1 w _i r

—* r—* i

0.02

0.01

0 0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

He a. H = Sea level

Figure 47. The effect of the SOM store on trim drag.

128

STM CONFIG STORE CM CC G 3 PYL0NS*370TRNKS «48311 33C O 22 SOM 52311 33C

AEDC-TR-74-75

H*l0.000 U. Id

A II U. 11

ft 1ft U. 1U

ft no U.Us

0.08

0.07

^Otr i m 0.06

r

j j

i ^A

0.05 J \ l r

0.04 Y* /

f l^

0.03

0.02

0.01

n 0.5 0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 1.14

129

AEDC-TB-74-75

SYH CONFIG STORE CM CC □ 21 PYL0NS+370TRNKS 48311 33C O 22 SOH 52311 33C

H=20.000 U. id.

f\ 1 1 U. 11

n in U. 1U

0.09

0.08 UH I

0.07

0.06

r

{•

0.05 0

P

0.04 EJ

0.03

0.02

0.01 ■■

0 0.5 0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 1.4

130

AEDCTR-74-75

STM CONFIG STORE GM CG B 21 PYL0NS+370TRNKS 48311 33C O 22 SOM 52311 33C

H=30.000 u. \c

0.11 ,

0.10

0.09

0.08 t s* >— ^t )

f 0.07

cOtrim 0.06

j f

/ J < f X*

i \ , ( r r

0.05 \ J—* LJ

0.04

n na U.UJ -

0.02

0.01

0 0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

K 'CO


131

AEDC-TR-74-75

SYM CONFIG STORE GW CG □ 21 PYLONS*370TANKS 48311 33C O 23 ERSH «9683 33C

0.12

0.11

0.10

0.09

0.08

0.07 cDtrim

0.06

0.05

0.04

0.03

0.02

0.01

H=SER LEVEL

— =^.—o

0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4 I«,

a. H = Sea level Figure 48. The effect of the Stubby HOBOS store on trim drag.

132

STH CONFIG STORE GN CG D 21 PYUJNS*370TRNKS U83U 33C 0 23 ERSH 49683 33C

AEDC-TR-74-75

rMO.OOO U.ld

nil U. 11

n in U. 1U

n no u.uy •

0.08

0.07

^Otr i m 0.06

r—< )

s* r- —«= «—- —( 1 J H

0.05 r GL

0.04 t f i s » J I

0.03 **^! ■

Ö ff V r 0.02

0.01

0 0.5 0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 1.4

133

AEDC-TR-74-75

STM □

CONFIG STORE GH CG 21 PYLONS*370TRNKS 48311 33C 23 ERSH 49683 33C

H=20,000 u. \<:

nil U. 11

n in U. 1U

0.09

0.08

0.07 c0trim

0.06 Vft

0.05 I

\ß 0.04

iß

0.03 ■

0.02

0.01

0 0.5 0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 1.4

134

SYM CONFIG STORE GM CG

□ 21 PYL0NS*370TflNKS 48311 33C O 23 ERSH «9683 33C

AEDC-TR-74-75

0.12

0.11

0.10

0.09

0.08

0.07

Cotr i m 0.06

0.05

0.04

0.03

0.02

0.01

H=30.000

( \

1 \

\

\ 1

s \

/ET

Q

ßy

0.5 0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 1.4

135

AEOC-TR-74-75

SYM □ o

CONFIG STORE GW CG 21 PYL0NS+370TANKS 18311 33C 2M TCTV 50811 33C

H=SER LEVEL U. Id

nil U. 11

n in U. 1U

n no u.uy

n no O.UÖ

n m U.U/

Cotrim 0.06

6 'A >—

n nc ¥ U.LD

n mi JB

U.U4

n riQ TLü

U. UJ —^ I-*

n no U.Uif

ft ni U.U1

0 1 0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 l.H

a. H = Sea level Figure 49. The effect of the TCTV store on trim drag.

136

AEDC-TR-74-75

STM □ o

CONFIG STORE CM CG 21 PYL0NS*370TANKS «8311 33C 24 TCTV 50811 33C

H=i0.000 u.i«:

nil U. 11

n ift U. 1U ■

0.09

0.08

0.07 cDlrim

0.06 >

A ,

0.05 A*}

0.04 r l. s

Jill

J0n

0.03

0.02

0.01

0 0.5 0.6 0.7 0.8 0.9 1.0 1.1

b. H - 10,000 Figure 49. Continued.

1.2 1.3 1.4

137

AEDC-TR-74-75

SYH CONFIG STORE GW CG D 21 PYL0NS+370TANKS 48311 33C © 24 TCTV 50811 33C

H=20.000 u. \c

n ii U. 1 I

0.10

0.09

0.08

0.07

0.06 Qy

0.05 3f

0.04 H3

0.03

0.02

0.01

0 0.5 0.6 0.7 0.8 0.9 1.0 1.1

Mco


1.2 1.3 1.4

138

STM CONFIG STORE CM CC □ 21 PYL0NS*370TflNKS 48311 33C O 24 TCTV 50811 33C

AEDC-TR-74-75

0.12

0.11

0.10

0.09

0.08

0.07 cDtrim

0.06

0.05

0.04

0.03

0.02

0.01

H=30.000

V T =±==1==== =\======= ==1=======

j£ ~xt it ^W-

± 0.5 0.6 0.7 0.8 0.9 1.0 1.1

Moo


1.2 1.3 1.4

139

AEDCTR-74-75

SYN CONFIG STORE CM CG 0 21 PYLONS*370TRNKS M831I 33C O 25 PF MOO WPN P 53511 33C A 26 PF MOD WPN UP 53611 33C

H=SEA LEVEL U. id

nil U. 11

n in U. 1U

0.09

0.08

0.07 cDtrim

0.06 ä

s* r-

0.05 / < u

f

0.04 M r u *

V *

0.03 r —i )-* r

0.02

0.01

0 0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 l.U

a. H = Sea level Figure 50. The effect of the PF Modular Weapons stores on trim drag.

140

AEDC-TR-74-76

STM

▲

CONFIG STORE GM CC 21 PYL0NS*370TANKS (18311 33C 25 PF MOD WPN P 53511 33C 26 PF H00 WPN UP 53611 33C

H=10.000 U. Id

|

nii 1 U. 11

0.10

0.09

0.08

0.07 cOtrim

0.06 i

0.05 1 %

[3

0.04 r l

0.03 -^

0.02 .

1

0.01

0 1 0.5 0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 1.4

141

AEDC-TR-74-75

STM CONFIG STORE GW CG D 3 PYLONS+370TPNKS 48311 33C 0 25 PF HOD WPN P 53511 33C A 26 PF MOD HPN UP 53511 33C

H=20.000 u. \c

ft 11 u. 11

n in U. 1U

ft ftQ u.ua

0.08

0.07 cOtrim

0.06

Vf

0.05 P

0.01 GJ

0.03

0.02

0.01

0 0.5 0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 1.14

142

AEDC-TR-74-75

SYM Q 0, A

CONFIG STORE GM CG 21 PYL0NS+370TRNKS «18311 33C 25 PF MOD WPN P 53511 33C 26 PF MOD WPN UP 53611 33C

H=30.000 U. Id

n 11 U. 11

n in U. IXJj 1 { 0.09 \

\

0.08 \ i \

i

0.07 CQtr i m

0.06

\ &/

\

& El

0.05 m Q

0.04

0.03

0.02

0.01

0 0.5 0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 1.4

143

AEDC-TR-74-75

SYM CONFIG STORE GM CG Q 21 PYLONS*370TRNKS 48311 33C O 29 ONEWAY RPV 54311 33C

0.12

0.11

0.10

0.09

0.08

0.07 c0trlm

0.06

0.05

0.04

0.03

0.02

0.01

H=SEA LEVEL

<*

i f f*l/

JLJ

( > J3)

T —t ¥-*■ Y

0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4 Moo

a. H = Sea level Figure 51. The effect of the Oneway RPV store on trim drag.

144

SYH CONFIG STORE ON CG Q 21 PYLONS*370TRNKS 48311 33C O 29 ONEWRY RPV 54311 33C

AEDC-TR-74-75

rMO.OOO u. It

nil U. 11

0.10

0.09

0.08

0.07

^Dtrim 0.06

r

0.05 M

cv

0.04 (

\ v J0>

0.03

0.02

0.01

0 0.5 0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 1.4

145

AEDC-TR-74-75

SYK CONFIG STORE GH CG Q 21 PYLONS+370TRNKS 4831! 33C © 29 ONEWRT RPV 54311 33C

H=20.Q00 U. Id

nil U. 11

0.10

0.09

0.08

0.07 c0trim

0.06

0.05 AD

0.04 ci i

** y-* T~f

0.03

0.02

0.01

0 0.5 0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 1.14

146

AEDC-TR-74-75

SYM CONFIG STORE GW CG Q 21 PYLONS*370TRNKS 118311 33C O 29 QNEWRY RPV 5U311 33C

0.12

0.11

0.10

0.09

0.08

0.07

Coir i m

0.06

0.05

0.04

0.03

0.02

0.01

H=30,000

j

T i \t it A x x vi IIX it \ 1 0 \ ,J^"(>'"""!

\ /X^ \ (K n lA^äf 4- V ^^ß

NL_tr

0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.1


147

AEDC TR-74-75

SYM CONFIG STORE CW CO □ 21 PYL0NS*370TANKS »18311 33C O 30 ERV 53311 33C

0.12

0.11

0.10

0.09

0.08

0.07

Cotrim 0.06

0.05

0.04

0.03

0.02

0.01

H=SEfi LEVEL

■

! 1 i

.—<»

/ ^-n \~r^^" | / pf

?j ?\f

<>— -\.Ar y 1 () PJ

11 HH|r j r

-^

0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4

a. H = Sea level Figure 52. The effect of the ERV store on trim drag.

148

STM CONFIG STORE CM CG □ 21 PYL0NS+37OTRNKS 48311 33C O 30 ERV 53311 33C

AEDC TR-74-75

HMO.OOO u. \c i

1

nil U. 11

0.10 |

0.09 i

0.08 !

0.07

^Dtr i m 0.06

y^\

A i i f L»-i i

0.05 0

0.Q4 < ,

y^^ rjjt

0.03 M i

0.02

0.01

i

0 1 Ö.5 0.6 0.7 0.8 0.9 1.0 l.l


1.2 1.3 1.4

149

AEDC-TR-74-75

SYM CONFIG STORE GM CG G 21 PYL0NS*370TANKS 48311 33C 0 30 ERV 53311 33C

0.12

0.11

0.10

0.09

0.08

0.07

^Dtr i m 0.06

0.05

O.OU

0.03

0.02

0.01

H=20.000

^--—H* ~xr IE \ J p i

13 \ //

VV J2 IT X ^^gr NtorfA iJ-^O-i'

0.5 0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 1.4

150

SYM CONFIG STORE GH CG Q 21 PYL0NS+370TRNKS 48311 33C O 30 ERV 53311 33C

AEDC-TR-74-7B

H=30.000 u. \c

0.11

n in U. 1U 1 { n no \ u.uy

\

n no \

V U.Ua \

n m \ p ^ y

U.U/

^Dtr i m n nc

1

r (

PJ U.Ub

n nc tfl Q

U.UO

n nn U.U4

n n^ U.UJ

n no U.Uc

n m U.ul

n 0.5 0.6 0.7 0.8 0.9 1.0 1.1


1.2 1.3 1.4

151

AEDC-TR-74-75

'CONFIG 21 PYLONS ♦ 370 GAL TANK

0 08

cD

0 07

0.06

005

0.04

•— cL "0 3-1

-

_ - LL. 01 [—1 □

DN- 17 72 i /? i . / i-CONFIG 22 (SOM)

, —

1 1 -CONFIG 21*1

y^l 1

IX '

c 1— -M^T i _ . 1

0.08 cD

0.07

0.06

0 05

0.04

ON • 3 97 I

i

1 CO MFIG 23 (ERSHH 1 1 J—:— 1

v- 3^CCONFIG'21*

£\

^=£=&^\

0 06 cD

0.07

0 06

0.05

0.04

0 g. 9 54

cc NFK 24 (TC TV)

1^ -co

" ?

,/ ^ IFIG

f» 21

A r <i/

~A f < A 5 I- — — \ '

0.08 cD

0.07

0 06

0 05

0.04

I I I I I I .CONFIG 25 (PHILC0 FORD) MOD WEAPONS POWERED)

.CONFIG 26 (PHILCO FORD MOD WEAPONS UNP0WERED1-

Figure 53. Drag characteristics and drag numbers for various external stores.

152

AEDCTFt-74-75

•CONFIG 21 PYLONS + 370 GAL TANK

0.08 CD

0 07

0 06

0.0 5

0 04

•— |

CL* 03 i • —

1 i

mm

1 V 0.3 •

nm 1 CONFIG 27 (NARC CLASS m)-i —0 1 1

! ON = 9 27 1 1 1 1^,

1 ' ' :z\ 1 1

1 W X y?_ -CONFIG 21'

1 1 c/

1 1

i riß

yCZ^-r— — II , i i i 0 08

CD

0 07

0.06

0 05

0 04

0 08

CD

0 07

0 06

0 05

0.04

1 1 1 i DN« 9 27 CONFIG 28 {NARC CLASS II) —

1^-

i A / ! \i A rL ■CONFIG 21'

.£. •i c/ i

J- 1—< «a —

II i i

\

DN- 10 60 C )NFI 3 2 » (ONE WAY RPV ) —

1 «^- >^ 1

A V 1 j A-? co (FIG 21*

I ! . i

~\ ' 1

j-j: 1 Jy^l,

1 1 1

0.08

CD

0 07

0.06

0 05

0.04

ON« 10 60 CONFIG 30 <EF V)- ^

,/ ^ "T Q

/. a S r£ CONFIG 21*

/ c/ 0— ir ' V /. 1 -f-n -

0.5 0 6 0 7 0.8 0 9 1-0 I.I 1.2 1.3

Figure 53. Concluded.

153

AEDC-TR-74-75

O PREDICTI0NSCREF.3I

A PREDICTIONS (REF. 2) O WIND TUNNEL RESULTS

H = 10,000 FT eg ■ 0.33C

0.07

«Of rim 0.06

O.OS

0.04

0.03

0.02

1

GW 49,683 u 1

0.6 0.7 0.8 0.9 1.0 I.I 1.2 1.3 Mm

a. Configuration 23 (ERSH)

CDfri

0.07

m. 0.06

0.05

0.04

0.03

GW 50,811 \ i

f f> y h

feQ^ f 0.6 0.7 0.8 0.9 1.0 I.I

b. Configuration 24 (TCTV)

0.07

'trim

.2 1.3

GW 53,311

^5»0

1 /

k^ »_ d "-■i

0.06

0 05

0.02 0.6 0.7 0.8 0.9 1.0 I.I 1.2 1.3

c. Configuration 30 (ERV) Figure 54. Comparisons of measured and predicted drag.

154

AEDC-TR-74-75

STN CONFIG STORE CM CC G 21 PYLONS*370TANK5 48311 33C O 22 SON 52311 33C

H«30.000 u

_ -0.004 L«6s

-0.008 nt P n ntol w- •m. = =| h yl i ft -f> A I

-U.UIe -1 \-

-0.016 H=20 .01

r -0.004

-0.008

-0.012

-0.016

i k K —i H N *J F M -^^

tx w l- r

. -0.004 Cm6s

-0.008

-0.012

-0.016

H=10.000

L«fcs

j>a -0.012<fc = a"-< ^ kU fi tl & =e< fc -£■?*

Slr-

^np**s™p ==^

H =SEfl LEVEL

*= = = -)

6 7 8 9 10 11 12 13 14x10-'

a. Stabilst or power Figure 55. The effect of the SOM store on the longitudinal control characteristics.

155

AEDC-TR-74-75

SYH CONFIG STORE CM CC Q 21 PTLONS*370TflNKS 48311 33C O 22 SON 52311 33C

0.012j H»30.000

1

„ 0.008,

0.001

SL 1-

\A 1 1HDJ

0 ]

H=2G .000 0.016

. 0.012 H.6S

0.008

0.001

0

0.012

„ 0.008, F CL6S

0.004

0

0.012

0.008 CLBS

0.004

i

^ *•*. ^> d N <! n to f A M [y

l r '

V

H= 10 .0 00

1- Wr i i

\j n H=SEfi LEVEL


156

AEDCTR-74-75

SYH CONFIG STORE CM CC G 21 PYLONS*370TRNKS 48311 33C 0 23 ERSH 119683 33C

0 H-30.000

r -o.oou

-0.008

-0.012« cf ^

-0.016 H=20 .000

r -0.004 c«6s

-0.008

-0.0I21

-0.016 0

r -0.004 cm6s

-0.008

-0.012

-0.016 0

r -0.004 c»6s

-0.008

-0.012

-0.016

0 & » n R <>x

^

H» 10 ,000

H= SE fi 1

^

(qpoo -^ r

8 9 10 11 12 13 14x10-»

a. Stabilator power Figure 56. The effect of the Stubby HOBOS store on the longitudinal

control characteristics.

157

AEDC-TR-74-75

SYN CONFIG STORE ON CG Q 21 PT10NS«370TRNKS 48311 33C O 23 ERSH (19683 33C

0.012

, 0.008 «Us

0.004

0

0.016

r 0.012

0.008

0.004

0

0.012

. 0.008 cLBs

0.004

0

0.012

0.008

0.004

H=30.000

p —■ =s H H k

^ h 1 Bf A \- ■=

I r ii

\ m

k d. H=2C .01

=1 1 l'7

1 H= 10 .01

H=SER LEVEL

M fttn^nTTm 9 10 11 12 13 14x10-'


158

AEDC-TR-74-75

SYM GONFIG STORE CM CC G 21 PYLONS* 370TANKS «18311 33C 0 24 TCTV S0811 33C

H*30.000

_'

H=20.000

-1 fe -jo— . _^h

"TT tqp^-*— 1 1

H»l0.000

^ -0.00H

-0.008

-0.012

-0.016

0

. -o.ooy Hi6s

-0.008

-0.012

-0.016

0

r -o.oon C«63 -0.008

-0.012

-0.016

0

. -O.OOil

-0.008

-0.012

-0.016 6 7 8 9 10 11 12 13 m»10->

a. Stabilator power Figure 57. The effect of the TCTV store on the longitudinal control

characteristics.

H= SE A 1

r ■ aa. SB ^N N J 8

159

AEDC-TR-74-75

STM CONFIG STORE CM CG 0 21 PTLOMS*370TflNKS «8311 33C 0 24 TCTV S0811 33C

0.012

. 0.008J*

0.004

r 0.012 H.6s

0.008

0.004

0 0.012

0.008 cL6s

0.004

0

0.012

0.008 CL6S

0.004

H-30.000

H=20.000

~~ —- H ft H L s r F p.

i ] B

H»l0.000

r- —4 s H 1 c I- ^—• —1 Hi W r *i ■4 1 ©*

H= SE n i

!5?5g§^uf =ar

B 7 B 9 10 1.1 12 13 14*10-»


160

AEDC-TR-74-76

STH C»riC STORE CH CO G 21 PYL0NS*37OTRNKS 46311 33C O 25 PF MOOHPNP 53S1I 33C A 26 PF MOD HPN UP 53611 33C

H-30.000

. -0.004 CM6S

-0.008

-0.012

-0.016

0

. -0.00«* c»6s

-0.008

-0.012

-0.016 0

„ -0.004 hrts

-0.008

-0.012

-0.016 0

. -0.004 cn6s

,( * A \

!■ a M u R s % *= s* J P i

& a 3 H*2C .01

E

H» 10 .01

H= SE fl 1

6 8 I 10 11 12 13 14x10-»

a. Stabilator power Figure 58. The effect of the PF Modular Weapons stores on the

longitudinal control characteristics.

161

AEDC-TR-74-7 5

STH CD O A,

CONFIG STORE CM CG 21 PU.0NS*370TqNKS 48311 33C 25 PF MOD HPN P 53511 33C 26 PF MOD HPN UP 5361I 33C

0.012

_ 0.008 H.63

0.004

0

0.016

r 0.012 cL6s

Ö.008

0.004

0

0.012

_ 0.008 4.63

0.004

0

0.012

0.008 CL6s

0.004

H-30.000

IE 9 »« J H H M<r & A J— —■ ** 3 [ V i I

H=20 .01

^2 -ak. !AV«>> ■*4H 1 1 W

H= IG .01

H=SER LEVEL

!^^-^??iS*§E==5i

7 8 9 10 11 12 13 14»10-'


162

AEDC-TR-74-75

STH

0

CONFIG STORE CH CC 21 PYL0NS*370TfiNKS 4831! 33C 29 ONEMPT RPV 54311 33C

H=30.000 u

r -0.004

-0.008 Q

-0.012

-0.016 H=2C .01

r -0.004 hn&s

-0.008

-0.012

-0.016

0

. -0.004

-0.008

-0.012

-0.016

0

r -0.004 C«6S

-0.008

-0.012

-0.016

h- H A O.. > 1 *l XZJ* =»

H= 10 .0

H= SE n i

6 7 8 9 10 11 12 13 14x10-'

a. Stabilator power Figure 59. The effect of the Oneway RPV store on the longitudinal


163

AEDC-TR-74-75

SYM CONFIG STORE GM CG O 21 PTL0NS«370TqNKS 48311 33C O 29 ONEMfiT RPV 54311 33C

0.012 H-30.000

<a 0.008. a fa iJF cL6s ' 0.00(1

-< H r >\ n~-

0 H=20 .000

0.016

r 0.012 cL8s

0.008

0.00(1

0

0.012

IF"™5§^JSS§^

H=10 .000

0 0.012

_ 0.008 cLBs

0.004

CL60.008,P = S^^^8

0.004

«IP

H=SEA LEVEL

IE::3^||S3^>I

6 7 8 9 10 11 12 13 14x10-«


164

AEDC-TR-74-75

SYH CONFIG STORE GM CG Q 21 PYLONS* 370TWWS M83U 33C O 30 ERV 53311 33C

H=30.000

r -0.004 cm6s -0.008

-0.0121*

-0.016 0

. -0.00« HaBs

-0.008

-0.012

-0.016 0

r -0.004 cm6s

-0.008

-0.012

-0.016

0

r -0.004 cm6s

-0.008

-0.012

-0.016

i H J— ^^kwfi^tlsl_

5» «f A

H=20.000

& >- ■Hi H H 1FT in & =»

^ A 1 y$ 4 F=

H= 10 .01

H=SEA LEVEL

6 8 I 10 11 12 13 14x10-'

a. Stabilator power Figure 60. The effect of the ERV store on the longitudinal


165

AEDC-TR-74-75

SYN CONFIG STORE GH CC Q 21 PYLONS*370TPNKS 48311 33C O 30 " ERV 53311 33C

0.012 H-30.000

-

0.008, cL6s

0.004

h W -^f-

0 H=20 .000

0.016

r 0.012 CL6S

0.008

0.004

0

0.012

CL6: 0.008 s 0.004

0

0.012

„ 0.008 cL6s

0.004

ir

lE&sp:

H=10 .000

m% 8*f=Si

H=SER LEVEL

!3@§pläE=ä3i

6 7 8 9 10 11 12 13 14x10-«


166

AEDC-TR-74-75

Table 1. Aerodynamic Coefficient Precision

M. q^psf ±ACm ±ACL ±ACt

0.60 630 0.0021 0.0056 0.0012

0.80 785 0.0017 0.0038 0.0010

0.85 810 0.0016 0.0036 0.0010

0.90 860 0.0016 0.0034 0.0010

0.925 875 0.0015 0.0032 0.0010

0.975 875 0.0015 0.0031 0.0010

0.975 890 0.0015 0.0029 0.0010

1.025 920 0.0015 0.0027 0.0010

1.10 960 0.0014 0.0024 0.0009

1.30 1025 0.0013 0.0020 0.0008

167

AEDC-TR-74-75

NOMENCLATURE

Ap Total wing-mounted store or store plus suspension equipment frontal area,

ft*

BL Buttock line from plane of symmetry, in.

Co Drag coefficient, drag/qJS

Cn* ■ Drag coefficient at trim conditions

CL Lift coefficient, lift/q^S

CL Slope of lift coefficient versus angle-of-attack curve at trim conditions, per degree

CL8 Slope of lift coefficient versus stabilator angle curve at trim conditions, per degree

Cm (0.3 3c) Pitching-moment coefficient referenced to 33 percent of the mean aerodynamic chord and WL 1.55, pitching moment/q^Sc

Cma Slope of pitching-moment coefficient versus angle-of-attack curve at trim conditions, per degree

Cmfi Slope of pitching-moment coefficient versus stabilator angle curve at trim conditions, per degree

c Theoretical mean aerodynamic chord (MAC) (see Fig. 3), 9.625 in.

eg Center-of-gravity location, percent MAC

DN Store or suspension equipment drag number defined as the increment in drag coefficient at M^ = 0.5 due to the total number of stores times the full-scale wing reference area (530 ft2) times 10 divided by the total number of stores, ft2 /store

FS Fuselage station, in.

GW Aircraft plus stores gross weight, lb

168

AEDC-TR-74-75

H Altitude, ft

M Free-stream Mach number oo

NP Neutral-point location, percent MAC

ANP Incremental change in neutral-point location at CL = 0.2 caused by external stores (neutral-point location of configuration X at CL = 0.2 minus the neutral point of the baseline configuration at CL = 0.2), percent MAC

ANPtI Incremental change in neutral-point location due to external stores at trim conditions (neutral-point location of configuration X at trim conditions minus the neutral-point location of the clean configuration at trim conditions), percent MAC

ANPx Incremental change in neutral-point location due to the addition of external stores (neutral-point location of configuration X minus the neutral-point location of configuration Y), percent MAC

q^ Free-stream dynamic pressure, psf

S Wing reference area, 1.3250 ft2

WL Waterline from reference horizontal plane, in.

a Wing chord angle of attack, deg

ctw tr Wing chord angle of attack at trim conditions, deg

6Str Stabilator angle at trim conditions, deg

169

j^tjüir aedc-tr-74-75 afatl-tr-74-113 effect of …carry, launch, and/or deliver a wide variety of...

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