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CURVED FLOW WIND TUNNEL TEST OF F-18 AIRCRAFT Frederick H. Lutze ABSTRACT The curved flow capability of the Virginia Tech Stability Wind Tunnel was used to investigate the lateral-directional characteristics of an F-18 aircraft. This report deals with a description of the model, the proced- ures used to obtain and correct the data and a graphical presentation of the results. The results include graphs of lateral-directional derivatives versus sideslip or static plots, the lateral directional static stability derivatives versus angle of attack, and finally the lateral-directional derivatives versus non dimensional yaw rate for different angles of attack and sideslip. Results are presented for several configurations including complete, complete without vertical tails, complete without horizontal tails, fuselage-wing and fuselage alone. Each of these were tested with and with- out wing leading edge extensions. In addition results of deflecting the basic control surfaces were investigated. A brief discussion of the results is included highlighting unusual characteristics.

ACKNOWLEDGEMENTS The compilation of the large amount of data associated with this project could not be done without the aid of several assistants. Special mention should be given Don DeGutz, Richard Goff, Howard Gofus, Diane Liebenow, Sandra Merritt, and TomTrimbath. Without their committment to the program and long hours of work, aquisition of the data required for this report would have been impossible. The funds for this research were provided by NASALangley Research Center under Contract NASI-15080 Task Authorization Number 8.

ii TABLE OF CONTENTS Page _ Abstract ........................................................... i Acknowledgements................................................... ii Table of Contents .................................................. iii List of Tables ..................................................... iv List of Figures .................................................... iv List of Symbols .................................................... vii Introduction....................................................... l iii LIST OF TABLES Table Title Page 3 Curved Flow Parameters ................................ 31 - LIST OF FIGURES Figure Title Page 2 Sketch of Basic Model 33 3 LongitudinalCharacteristics - Configurations 1,9,10 .. 34 4 LongitudinalCharacteristics - Configurations 13,14, 5 LongitudinalCharacteristics - Configurations 1,2,3 ... 40 6 Variationof Static Lateral-Directional Character- istics With Angle of Sideslip - Configurations 1,6, 7 Variationof Static Lateral-Directional Character- istics With Angle of Sideslip - Configurations lO, 8 Variationof Static Lateral-Directional Character- istics With Angle of Sideslip - Configurations I, i 9 Variation of Static Lateral-Directional Character- istics With Angle of Sideslip - Configurations I, iv Table Ti tl e Page I0 Variation of Lateral-Directional Static Stability ^ II Variation of Lateral -Directional Static Stability 12 Variation of Lateral-Directional Static Stability 13 Variation of Lateral -Directional Static Stability 14 Variation of Lateral-Directional Static Stability 15 Variation of Lateral-Directional Static Stability Derivatives with Angle of Attack and Sideslip, ^ 16 Variation of Lateral -Directional Static Stability Derivatives with Angle of Attack and Sideslip, = - 0.0253 ....................................... III 17. Variation of Lateral-Directional Static Stability Derivatives with Angle of Attack and Sideslip, 18 Variation of Lateral -Directional Static Stability Derivatives with Angle of Attack and Sideslip, • 19 Variation of Lateral-Directional Static Stability Derivatives with Angle of Attack and Sideslip, Table Ti tl e Page 20 Variation of Lateral-Directional Static Stability 21 Variation of Static Lateral-Directional Stability 22 Variation of Static Lateral -Directional Stability 23 Variation of Static Lateral -Directional Stability 24 Variation of Static Lateral -Directional Stability 25 Variation of Static Lateral -Directional Stability 26 Variation of Static Lateral -Directional Stability 27 Variation of Static Lateral -Directional Stability 28 Variations of Static Lateral -Directional Stability 29 Variation of Static Lateral-Directional Stability 30 Variation of Static Lateral-Directional Stability 31 Variation of Static Lateral-Directional Stability Derivatives with Yaw Rate, Configuration 7 ........ 265 , , 32 Variation of Static Lateral -Directional Stability vi LIST OF SYMBOLS AF Projected frontal area of model perpendicular to wind tunnel axis (m2) A Projected area perpendicular to x body axis (m 2) x A Projected area perpendicular to y body axis (m 2) Y A Projected area perpendicular to z body axis (m 2) z b Wing span (m) Wing mean aerodynamic chord (m) Cl,C2,C 3 Shape constants given in Table 2 CD = D / qS Drag coefficient CL : L / qS Lift coefficient C_ = L / qSb Roll moment coefficient Cm : M / qSc Pitch moment coefficient Cn = N / qSb Yaw moment coefficient C = Y / qS Side force coefficient Y D Drag (N) F Fuselage Fn Parameter defined on page 8 H Horizontal Tail L Lift (N), roll moment LEX Wing leading edge extensions ,]_ M Pitch moment (Nm) N Yaw moment (Nm) p Pressure (N / m2) Dynamic pressure (N / m2) " vii R Radius of tunnel calibrated curvature (N) r Yaw rate (rad / sec) = rb / 2V Non-dimensional yaw rate S Wing area (m2) V Speed (m / sec) V Vertical tails W Wing XCB Distance from reference point to center of volume (m) Y Side force (N) Angle of attack (deg) B Angle of sideslip (deg) Blockage correction factor aa Aileron deflection, positive right aileron down (deg) ad Horizontal tail differential deflection, positive right tail trailing edge down (deg) af,_e Wing leading edge flap deflection (deg) af,te Wing trailing edge slap deflection (deg) ah Horizontal tail deflection, positive trailing edge down (deg) ar Rudder deflection, positive trailing edge left (deg) p Air density (kg / m 3) viii INTRODUCTION Currently there is a strong interest in the dynamic stability of aero- space vehicles. In order to obtain a better understanding of this phenomena, many types of wind tunnel, free flight, and flight tests have been devised.

A recent AGARDconference, devoted solely to this aspect of flight mechanics, summarizes the current work being done in this area.l Reference 1 cites several research topics related to this problem which need further investi- gation. Included in these topics are the need for separation of rotary and unsteady aerodynamic derivatives and the need for determining dynamic cross coupling derivatives. These effects seem to be of particular interest for vehicles at high angle of attack. Consequently a considerable amount of re- search has been concentrated in the range of high angle of attack studies.

Several methods of testing have been used in an attempt to provide the required data. Included in these techniques are oscillating and free flight tests, 3 and rotary balance methods.4 Another method, developed at NASALangley and now implimented at V.P.I., is that of curved flow. In this method the model is immersed in a curved flow with the appropriate velocity profile necessary to simulate flight in a curved path. 5'6'7 From this type of test the pure rotary derivatives can be obtained in a steady state environment. Furthermore standard wind tunnel procedures can be used for data aquisition and blockage corrections. In addition the steady state environment permits ease of implimenting flow visualization techniques. The range of angles of attack that can be tested is limited only by the method - used for support. A description of the wind tunnel, its calibration and necessary corrections for reducing data are discussed in reference 8.

This report presents the results of testing an F-18 fighter aircraft model in the curved flow test section in the VPI&SU Stability Wind Tunnel. _ Lateral data are presented for four curvatures associated with four yaw rates as well as for straight flow. For each curvature data are presented ., for several configurations allowing the contributions of each appendage to be assessed and allowing the interaction of the curved flow on the various appendages to be observed. A brief discussion of the results is presented emphasizing the salient aerodynamic characteristics obtained.

APPARATUS, MODEL,TEST TECHNIQUE Wind Tunnel The tests were conducted in the square 1.83 x 1.83 m (6 x 6 ft.) test section of the Virginia Tech Stability Wind Tunnel located in the Depart- ment of Aerospace and Ocean Engineering. The nominally square test section has vertical walls which are designed to have enough flexibility so that they may be deflected into a curve, creating a curved air flow past the model.

Jack-screws positioned at regular intervals along each wall allow the curva- ture to be set at prescribed values In order to complete the simulation of flight in a curved path it is necessary to redistribute the velocity pro- file in the radial direction. This is done by installing wire screens, varying in mesh across the wind tunnel, upstream of the test section. The mesh size varies so that the densest portion is located toward the center of curvature. A sketch showing a typical curved flow test arrangement is pre- sented in Figure I. Details of curved flow theory, calibration and tunnel operation are given in Reference 8.

Balance , The forces and moments were measured by the use of an internally mounted strain gage balance. Two separate balances were used, one for the longitudinal measurements, Langley balance #FF05, (normal and axial r forces, and pitch moment) and another for the lateral measurements, Langley balance #FF06, (roll and yaw moments, and side force). The balances were supplied by NASALangley Research Center and were compatible with the model. A nominal five volt power supply was used to supply power to the balances.

Calibration of the balances to account for system dependent varia , tions such as voltage supply and cable length differences was accomplished using a span check. Basically this check consists of applying the same load to the balance (via a precision resistor) in the local system as was used in the calibrating system and observing the system readout. An appropriate correction factor can then be determined and a calibration determined. The calibrations used throughout the tests were as follows: Normal force 56.3879 N / mV (12.6765 Ibs / mV Axial force 39.2244 N / mV ( 8.8180 Ibs / mV) Pitch moment 5.9187 Nm / mV ( 4.3654 ft Ibs / mV) Roll moment 1.8175 Nm / mV ( 1.3405 ft Ibs / mV) Yaw moment 11.7105 Nm / mV ( 8.6372 ft Ibs / mV) - Side force 32.4391 N / mV ( 7.2926 Ibs / mV) Data Aquisition System Data was obtained using a Hewlett Packard (HP) 3052 Data Aquisition System. This system includes an HP3455digital voltmeter, an HP 3495 " forty channel Scanner and an HP 9825 Calculator. Data was obtained accordingto the proceduresdescribedbelow, reduced and stored on tape.

Subsequentlyit was transferredto the University'sIBM 370 / 168 computer where it was sorted for the purposesof plotting the results.

Model The investigation was conductedwith a 0.07 scale model of the F-18 aircraft. The model, supplied by the Langley Research Center was specially built for these tests and was constructedto be compatiblewith the above balancesand sting support system. A three view sketch showing the general layoutof the model is shown in Figure 2.

The model was constructedin a manner that allowed variousparts to be easily removed to permit build-up tests of severalconfigurationsto be per- formed. In addition severalcontrol surfacescould be set in deflected positions. These includedwing leadingand trailingedge flaps, ailerons, rudderson the twin vertical tails. In addition the horizontaltail surfaces could bedeflected togetherorinadifferentmanner. The configurations tested along with their identifyingnumbers are given in Table I. It should be noted that the base configuration(#1) was the full configuration with the wing ieadingedge flaps deflecteddown 25 degrees. Unless otherwise stated, the leadingedge flaps were in the deflectedposition for all configurations.

In order to reduce the data to account for blockage effects, and in curved flow, to account for pressure gradient effects, it is necessaryto know the front, planform,and profile areas as well as the model volume for each configuration. These quantities along with the basic reference geometry are given in Table 2.

Test Procedure The model was mounted in the wind tunnel using a pylon supporting sting mount. By using a double dog-leg arrangement as shown in Figure I, it was possible to obtain angles of attack from 0 to 45 degrees. The pylon support was mounted on a turntable and slide arrangement to allow sideslip angles of _ I0 degrees while maintaining the model location in the center of the tunnel. (See Figure I) As the walls were curved for simulating increased yaw rates, the limited travel of the slide mechanism prevented obtaining positive side slip angles greater than 5 degrees. In fact at the largest curvature tested, the model had to be displaced 0.102 m (4 in.) off the centerline (toward the inner wall) to obtain the desired 5 degrees angle of sideslip. Corrections in mean velocity were made to ac- count for this shift.

The matrix of tests were completed by first selecting the curvature or yaw rate, then selecting the configuration, sideslip and angle of attack.

Hence angle of attack sweeps were done for each sideslip angle which in turn were swept for each configuration. Data for these tests were taken in the following manner. For each new configuration wind off as well as wind on readings were taken for each angle of attack at the first sideslip angle selected. The wind off valves were stored to be used for the same con- figuration at corresponding angles of attack for the remaining sideslip angles. Consequently the data taken at these remaining sideslip angles - were taken without shutting the tunnel down as the angle of attack sweeps were made.

, At each test point curvature, configuration, pitch angle and yaw angle were observed and entered into the data aquisition system. The static pressure, temperature, tunnel dynamic pressure (see below), and the six components of the strain gage balance were read on commandby the data aquisition system. These latter readings were obtained by taking the average of 15 samples taken over an 8 second time interval.

The test conditions in the wind tunnel were set by calibrating the pres- sure drop across the upstream contraction with the dynamic pressure in the empty test section for straight flow. The same pressure drop was used for the straight and curved flow tests. The values used for this test were a pressure drop of 0.044 m (1.71 in) of water which corresponds to a dynamic pressure of q = 766.08 N / m2 (16 Ibs / ft 2) in the unoccupied test section. This speed corresponds to a Reynolds number of approximately 6 x 105 based on the mean aerodynamic chord.

TESTS Tests using the longitudinal balance were carried out for the straight flow or non-yawing case only. Eight configurations were examined corresponding to the following numbers from Table I; configurations 1,2,3,9,10,13,14 and 15.

Tests were carried out for three sideslip angles of B = - 5, O, and 5 degrees and for I0 angles of attack from 0 to 45 degrees in 5 degree increments.

Lateral tests were performed for four different calibrated yaw rates in addition to straight flow. The four non-dimensional yaw rates rb / 2V = -0.0253, -0.0380, -0.0515, and -0.0707. Lateral tests were carried out for all configurations shown in Table 2 for all curvatures. Tests were run for F all angles of attack from 0 to 45 degrees in 5 degree increments at sideslips from -I0 to +I0 degrees sideslip in 5 degree increments. As noted previously sideslip angles only up to +5 degrees could be tested at the two highest _" yaw rates, rb / 2V = - 0.0380 and -0.0707. Exceptions to the above test schedule occurred for configurations 5, 16, 17, and 18. Configuration 5 was tested only in straight flow for full range of sideslip while config- urations 16, 17 and 18 were tested at all yaw rates but only at zero side- slip.

DATAREDUCTION Data recorded for each test included run number, curvature, configuration, pitch angle, yaw angle, local pressure, temperature, contraction ratio pres- sure drop, and six components of strain gage data with wind on and wind off (stored data). This data was reduced and printed out in the form of run number, configuration number, curvature, angle of attack, sideslip angle, corrected tunnel dynamic pressure, speed, Reynolds number, and the non- dimensional force and moment coefficients in both body and stability axes.

Included in this reduction are corrections in the tunnel dynamic pressure due to blockage effects and corrections for the lateral pressure gradient which occurs when the walls are curved. A brief discussion of these cor- rections is given below. More details can be found in References 8 and 9.

The blockage correction used is empirical but has been shown in the past to be adequate at the high angle of attack range and in addition is simple to apply. 6'9 The correction in the dynamic pressure is given by

qc= q (l +

where € = I / 4 frontal area tunnel area Thefrontal area depends upon angle of attack and sideslip and is given by

AF : (Ax cos _+ Az sin_) cos B + Ay Isin BI

where A , A and A are the projected areas perpendicular to the x y z x,y, and z body axes and are given in Table 2.

The correction for the lateral pressure gradient caused by curving the flow depends on the model volume and shape. Details involved in the develop- ment of these corrections are given in Reference 8. Important in these cor- rections are the model volume, approximating ellipsoid shape factors, and the value of the lateral pressure gradient. These values were established by direct measurements from the model and from tunnel calibration data and are given in Tables 2 and 3. The corrections used are defined as(corrected value) - _unnel value) = Avalue and given by the following: + aAxial

[(l (Vol)

2C2 ) " sin B cos _ - Fn cos B cos _] a__p_D . • aR AY = [(I + 2C1 COS 2 _ + 2C3 sin 2 _) cos B + Fn sin B] -_R " (Vol) ANorm = [(I + 2C2) sin Bsin _- Fn cos Bsin _] • a_p_ . (Vol) aR where Fn = [(C3-C I) cos2_+ (C2-C3)] sin 2 and Cl,C2,C 3 are the shape parameters in Table 2. An additional correction associated with the lateral pressure gradient must be made if the center of volume of the model does not coincide with the moment reference point under these circumstances a correction must be made to the yawing moment.

The change in apparent yawing moment is given by AN = Ay • XCB where XCB is the position of the center of buoyancy (center of volume) with respect to moment reference point. For this test this distance was assumed to be zero.

One final correction was made for the case of tests run with the largest curvature at + 5 degrees sideslip. As discussed previously physical limitat- ions of the tunnel prevented the model from being centered. Because of the velocity gradient, a small correction for the nominal dynamic pressure had to be included. In this case the dynamic pressure was 0.95 the dynamic pressure at the centerline and such a correction was included in the data reduction.

The final reduced data was obtained by taking the difference between wind on and wind off strain gage readings, applying the balance calibration factors, correcting the resulting forces for pressure gradient effects and dividing the corrected force and moment readings by the corrected dynamic pressure and appropriate geometric constrants to yield the proper force and moment coefficients.

.6 RESULTS AND DISCUSSION The results of the curved flow tests are presented graphically in Figures 3 thru 32. These figures include the standard static tests results as well as the results observed in the steady state curved flow. All results unless otherwise noted are presented in stability axes since the yaw rate simulated in the tunnel is about the Z stability axis. In the following discussion the significance of each figure will be discussed and the highlight associated with it pointed out. Possible phenomena associated with these highlights will be briefly discussed.

Figures 3, 4 and 5 present the longitudinal data of lift, drag and pitch- ing moment coefficient for several configurations; Figure 3 for configurations I, 9, and I0, Figure 4 for configurations 13, 14 and 15 and Figure 5 for con- figurations I, 2 and 3. Each figure contains results for -5, O, and 5 degrees sideslip.

Figure 3 shows that for the full configuration the vehicle shows gentle stall characteristics with the stall not occurring until 40 degrees angle of attack (AOA). These characteristics are the same for all configurations in- cluding the leading edge extensions (LEX). A considerable amount of lift (20%) is generated by the horizontal tail at AOAabove 20 degrees. The pitch- ing moment for the complete configuration shows a negative slope with an in- crease in AOAup to about 30 degrees after which the slope is zero. The tail- less configuration shows a marked positive slope after 5 degrees AOAremaining positive at a lesser amount above 20 degrees. There is virtually no effect of sideslip on any of the properties discussed above.

Figure 4 shows the effects of the LEX on fuselage-wing characteristics.

Of importance is the fact that without the LEX the wing-fuselage combination shows an abrupt stall at 20 degrees AOA. This would indicate that the smooth flow over the wing is probably disrupted and stall occurs at this AOA. The I0 effect of the LEX on this flow pattern can only be conjectured. One sus- pects that not only do the LEX contribute to the lift at high AOA but that the abrupt separation of flow over the wing is alleviated due to the LEX " _ trailing vortices since no break in the lift curve with LEX is observed.

However it must be assumed that some character of the flow changes at 20 degrees angle of attack if only at the wing tips.

Figure 5 shows the result of a 12 degree trailing edge up deflection of the horizontal tail as well as the effect of the wing leading edge flaps moved to a zero degree deflection. The elevator deflection shifts the moment and lift coefficient curves as expected. The positioning the leading edge flaps to the undeflected position reduces the lift coefficient considerably (5-10%) for AOAabove 20 degrees and increases the lift coefficient slightly (I - 5%) for AOAbelow 20 degrees. Again there seems to be little effect due to sideslip on these nominal results.

Figures 6 thru 9 are graphs of the lateral force and moment coefficients versus sideslip angle for AOA from 1 to 45 degrees in 5 degree increments.

Figures 6 and 7 are basically build up plots which show the effects of adding or removing various appendages while Figure 8 shows the effect of deflecting various surfaces.

Figure 6 shows the effects of removing the vertical tails and / or the leading edge extensions from the full configuration. At the low angles of _ attack it i s apparent that the LEX have little effect on roll, yaw or side- force change with sideslip angle. At 5 deg AOA the roll moment seems to be slightly effected by the presence or absence of the LEX, while yaw and side- force remain unaffected. Such behavior suggests asymmetric lift caused directly by the LEX or indirectly by their wake vortices flowing over the II wing. Withoutadditionalevidence it is probably the direct lift contri- bution. This choice is supportedby noting that the pitch moment becomes more positivewith the LEX than without (See Figure 4).

At lO degreesAOA the effects of the LEX start to show up in yaw and sideforceas well as in roll. Here the vehicle shows a little more weather- cock stability(CnB> O) with the LEX than without. The roll moment ex i libits unusualbehavior with sideslip. It appears the vertical fins have little effect on the roll moment, the curves with and without the vertical tails falling nearly on top of each other, for each case, with and without LEX.

At 15 degreesAOA the roll characteristics remain the same, showing little effect due to the vertical tails. The side force and yaw moment however show strong effects due to the vertical tails as exhibitedat lower AOA. For the full configurationthe yaw moment changes significantly when the LEX are re- moved. This effect is not observedwhen the vertical tails are absent in- dicating that interactionof the flow field generatedby the LEX and the vertical tails is occurring. In this case the interactionis favorablewith respect to stabilityin yaw.

The first significantly differentbehavior with and without the LEX occurs at 20 degrees AOA in the yaw moment. Here between 5 and lO degrees sideslip,the curve without the LEX changes its slope to negativewhile with the LEX in place the slope remains positiveand nearly constant. We would expect significantdifferencesbetween with and without LEX behavior to appear at this AOA since we observed the wing without the LEX to stall at this point. These same trends carry over to the 25 degree AOA case, Here the vehicle is marginallystable in yaw without LEX but stable with them, The rollmomentcharacteristics showsomechangesfromthe previous patterns at lowerAOA. Hereaddingthe vertical tailsand LEX decrease the effective dihedral (C_B< O) the largestincrement occurring when the LEX are added but an almostequivalent increment when the tailsare added. Including both LEX and tailsadds verylittleto the original increment of LEX or tails.

At AOA of 30 and 35 degrees, the vertical tailshavevirtually no effect on the rollingmomentbut enterintothe yaw momenteffects. The interaction of the LEX and the vertical tailcan be observed in the yaw momentgraphs, withoutthe LEX the tailsshowsignificant contribution to yaw momentleading to a more positive slopewith sideslip with the tailsin placethanwithout the tailsin place. With the LEX in placehoweverthisslopeis decreased for the caseof the fullconfiguration and increased for the configuration withoutthe tailso thatthe two curvesnearlycoincide.

Figure7 presents the resultsfor the fuselage, fuselage-wing, and fuse- lage-wing and vertical tail,the lattertwo with and withoutLEX. The results for low anglesof attackare similarto thosein the previous figureindicat- ing,as expected thatthe horizontal taildoesnot effectthe lateralforce and momentsat low AOA. At lO degreesAOA, however the effective dihedral is improved withoutthe horizontal tailbothwithand withoutLEX. Thisphenomena doesnot occurat 15 or 20 degrees AOA. In factthesecurvesare verysimilar to the corresponding curvesin the previous figure. At 30 degreeAOA the effectof the vertical tailson the rollmomentis virtually non-existant with- - out LEX and remains small with the LEX as in the previous figure. The results for the remaining AOA are similarto thosein the previous figure.

Figure8 showsthe effects of deflecting the leading and trailing edge flapson the wing as well as a horizontal taildeflection.Significant effects start to appear at 15 degrees AOA. Here both the roll and yaw moments show some decrease in stability when the leading edge flaps are not deflected.

The LEX reduce this effect somewhat. At 25 degrees AOA the behavior in roll and yaw are completely different for the non-deflected leading edge with and without LEX indicating a strong interaction between the LEX and the flow over the wing as observed previously. At AOAabove 35 degrees the effects of flap and horizontal tail deflections are reduced.

Figure 9 shows how the aerodynamic properties change with control surface deflections. At low AOAthe curves are shifted as expected with rudder de- flection producing a yaw moment with a slight roll moment and aileron deflect- ion producing a roll moment with a slight yaw moment. The differential tail produces only a small roll moment since the deflection is small (_ 5 degrees) and the surfaces are close to the roll line. As the AOA increases the aileron effectiveness is reduced until about 35 degrees AOAwhere the aileron produces about the same amount of roll as the rudder deflection. The differential tail deflection produces a roll moment in the opposite direction at 45 degrees AOA and at all sideslip angles.

Figure I0 is a summary plot of the B-sweep curves. The slopes were cal- culated by taking the difference between the coefficients at _ 5 degrees angle of sideslip and dividing the result by I0. Hence the units are "per degree."

In general it can be observed that the LEX have little effect on stability at the low AOA. At about I0 deg AOA the configurations with the LEX show con- siderable differences from the configuration without the LEX, The most notable ._ differences occur in the roll stability graph. The full configuration with the LEX shows a stronger dihedral stability until about 25 degrees AOAwhere the full configuration without the LEX shows increased stability. This trend holds for all configurations compared with and without LEX An ex- treme example of this type of behavior is shown for the configuration with _ the wing leading edge flaps up. Here at 25 degrees AOA, the roll stability is unstable with the LEX on and strongly stable with them off indicating an important interaction among the LEX shed vortices, their position on the wing, and the sideslip angle. As might be expected Figure I0 shows little effect on lateral-directional stability due to control surface deflections.

Figures II, 12, 13 and 14 show the same curves as Figure I0 for the various tunnel curvature settings or equivalent yaw rates. The general trends for all curvatures is the same as that for zero curvature. The effects of the LEX on yaw stability are to improve the stability up to about 20 degrees AOAand destabilizing for AOAabove 20 degrees. For the full configuration this trend occurs at all curvatures but the angle at which the switch takes place tends to increase with curvature with the switch taking place at 30 degrees AOAfor the largest curvature. Without the vertical tails the switch- ing point is more strongly defined and occurs at virtually the same AOA, 25 degrees, for all curvatures. The dihedral effect shows the same trends with the configuration with the LEX showing a marked improvement in stability up to about 25 degrees AOAand large reduction in stability above this AOA. The switching point is sharply defined for both the full configuration and the full configuration without vertical tails, with latter occurring slightly earlier (23 degrees AOA) than for the full configuration. These same trends are observed for the fuselage-wing and fuselage-wing and vertical tail con- figurations with and without LEX. Curvature effects on the wing leading edge flaps undeflected appear to be minimal, the same trends as discussed , i earlier occurring at all curvatures.

Figures 15 thru 19 are non-traditional stability derivative plots.

The purpose of these plots is to show the effect of curvature and sideslip on the lateral-directional stability derivatives. Each figure contains the information for all configurations at one curvature or yaw rate. Any one graph contains the stability derivative information for one configuration calculated by three different methods. The three methods used as numbered in the figures are: I. The standard method used in the previous figures where the derivative is obtained by evaluating the force or moment coefficient at + 5 degrees sideslip, taking the difference and dividing by I0, e.g. (Cx(5) - Cx(-5)) / lO 2. The use of just the positive sideslip and zero sideslip quantities to give (Cx(5) - Cx(O)) / 5 3. The use of just the negative sideslip and zero sideslip quantities to give (Cx(O) - Cx(-5)) / 5 It is clear that the first method is an average of the last two and always falls in the middle. In general at low angles of attack the three methods provide the same result. At high angles of attack this is no longer true in all cases. The cause for the difference has been shown in the past 7 to be associated with the asymmetric vortex shedding from the nose area _ , coupled with the interaction of these vortices with wing and tail structures.

The additional capability to curve the flow accentuates asymmetric flow either on the forebody or tail surfaces enabling one to isolate these effects.

In viewing these graphs the key features to observe are the spreading apart of the lines for any given coefficient. This spreading signals strong dependence of the stability derivative on sideslip angle. Furthermore if this spread straddles the zero line, then the static stability itself depends upon the sideslip angle. For the purposes of discussion we will refer to such a situation as being bistable. That is a vehicle is statically bistable if sideslips in one direction yield statically stable derivatives and sideslips in the opposite direction yield statically unstable derivatives. For con- venience we will refer to a vehicle as having even bistable behavior if positive sideslip gives stable stability derivatives or positive stability, and having odd bistable behavior if positive sideslip gives unstable stability derivatives or negative stability. Finally it should be pointed out that these definitions only hold for the _ 5 degree sideslip range used in these plots.

As observed in previous figures and to be observed in later figures the sign of a stability derivative can change from that in the 0 to 5 degree sideslip range to a different sign in the 5 to I0 degree sideslip range. With these preliminaries we can examine the highlights of Figures 15 thru 19.

In Figure 15 straight flow results are shown. For the full configuration with LEX virtually no effects of sideslip are observed until just below 30 degrees AOA at which time slightly even bistable behavior occurs in roll with no effect on yaw. In the 30-45 degree AOAregion sideslip dependence appears in both roll and yaw stability derivatives. Here, however, the roll stability is maintained for all sideslip angles while the yaw moment shows strong even bistable behavior between 33 and 43 degrees AOA. For the full configuration without the LEX a region of odd bistable behavior in yaw exists from 25 to 35 degrees AOA. Furthermore from 40 to 45 degrees AOAthe full configuration without LEX displays some even bistable behavior in yaw. In roll, on the - otherhand no bistable behavior is observed although strong sideslip depend- ence is observed from 15 to 45 degrees AOA. This dependence appears to be opposite that for the case with the LEX on in the 35 degree AOA region.

The remaining graphs in Figure 15 show the asymmetric properties for the remaining configurations with and without LEX in straight flow. The general trend is that the LEX greatly reduce the asymmetric effects and post- pone those that do occur to higher angles of attack. With the LEX on roll- ing moment generally shows little sideslip effects compared to the same con- figuration without LEX. With respect to yaw, the LEX postpone the effects due to sideslip. Furthermore there is a suggestion, but certainly not a rule.

that the effects are reversed at the higher AOA. The fuselage alone results are of interest since they indicate that asymmetric effects occur in the A0A region from 20 to 35 AOA in yaw and roll and from 20 to 45 degrees A0A in sideforce. It would be expected that some asymmetric nose vortices might occur for this fuselage shape and these results indicate they probably do occur. Finally the full configuration withundeflectedleading edge flaps shows a considerable difference in asymmetric effects with LEX on or off.

With the LEX significant asymmetric effects do not occur until 25 degrees AOEwhile without LEX they begin as early as I0 degrees AOA. It appears from the above observations that separated flow over the wings has a large contribution to the sideslip effects observed.

The effect of curvature on the lateral stability derivatives can be examined by comparing Figures 15 thru 19. If we initially look at the full configuration with LEX at the lowest curvature we can observe initial curvature effects. For a small amount of curvature the yaw and rolling moment curves show consistent effects in that the values computed by the I three methods don't cross as much as they did in straight flow. In par- ticular the y a w moment stability derivative tends toward odd bistable be- havior at I0 degrees AOA and actually achieves this behavior in the neigh- borhood of 25 degrees AOAand above 35 degrees AOA. This means that a sideslip producing a nose in toward the center of the turn or positive sideslip (recall the simulated turn in the tunnel is to the left) is de- stabilizing in yaw while a nose out attitude is stabilizing. The rolling moment stability derivative has this same odd bistable behavior for AOA between 30 and 40 degrees. At lower AOAthe vehicle is stable in roll but has a trend toward even bistability at AOAbetween 15 and 27 degrees. For the roll moment this same trend is maintained for all the curvatures, only the details of where the odd bistability starts and how strong it is change slightly. The yaw moment stability derivative on the otherhand is not so well behaved with curvature. As curvature increases the odd bistable be- havior at the lower yaw rates shifts to even bistable behavior at the higher yaw rates. The region of this type of behavior is always above 35 degrees AOE.

For the full configuration without LEX similar effects are observed but generally starting at a lower AOA. For the roll stability the extreme values occur at 25 degrees AOArather than 40 degrees. At the maximum curvature no bistable behavior is observed although the trend is still present. Further- more the trend with or without LEX for all curvatures is toward odd bistable behavior in roll. For the case of yaw stability some differences are observed for LEX on or off. With the LEX on we previously observed a change in the bistable behavior as curvature increased. Without LEX the trend is always toward even bistable behavior in yaw except at 45 degrees where it switches to odd bistable behavior for LEX on or off.

Without the vertical tails, the effect of curvature on the asymmetric yaw moment stability properties is small. All the curves show instability no matter how they were calculated. In addition, other than the cases for straight flow and the smallest curvature, asymmetric effects on yaw sta- bility were small. The roll moment stability curves exhibit similar be- havior as shown for the full configuration. The extreme effects occur at 35 degrees AOA for the lowest curvature and at 40 degrees for the larger curvatures. The bistable behavior is in the same sense as the full con- figuration. At the largest curvature the effect seems to be diminished somewhat from that with the vertical tails present. The same configuration without the LEX show limited asymmetric effects except at 25 degrees AOA in roll for the larger curvatures, and at 35 degrees AOA for the smallest curvature.

The most dramatic effects of curvature on asymmetry properties occurs when comparing the fuselage-wing and vertical tail with and without LEX.

With the LEX in place the stability curves for straight flow are well be- haved for both yaw and roll moments. The introduction of curvature causes increased asymmetric effects in both the roll and yaw moments. The extreme differences for positive and negative sideslip occur at 35 degrees AOA for the roll moment and 40 degrees for the yaw moment. When the LEX are removed 2O the asymmetric effects become more pronounced at lower AOA. In particular the effects occur at 15 degree AOA for the yaw moment and at 20 degrees AOA for the roll moment. Similar trends are displayed for the fuselage-wing configuration. At the greater curvatures the effects are somewhat dimin- ished over those at lower curvatures.

The fuselage alone indicates some asymmetric properties at zero curvature with little change at the lowest curvature. However increasing the curvature further shows large asymmetric effects in both roll and yaw moment stability.

Also the fuselage alone case shows large asymmetric effects on the side force which have not shown up in previous configurations.

The trends observed for the full configuration with flaps up for straight flow with LEX on and off are observed in the curved flow situation. The curva- ture tends to reduce the angle of attack at which the asymmetric effects start to occur. Finally if the trailing edge flaps are deflected down, there is little change from the undeflected case. Again large effects are noticed in roll at 40 degrees AOA. For yaw moment the curves are so close to zero at large AOA that even small asymmetric effects can lead to a bistable situation.

For the larger curvatures even bistability behavior is observed in yaw.

Figure 20 presents the lateral directional stability derivatives in body axes for straight flow only. These are included since a considerable amount of data in the literature is presented in body axes. Consequently these plots _. Would make quick comparison of data possible.

Figures 21 thru 32 are curvature or yaw rate sweeps for different con- figurations. Here the lateral forces and moments are plotted versus the non-dimensional yaw rate for the various sideslip angles. A considerable amount of information can be obtained from these plots including much of the material presented in Figures 15 thru 19. Lines that appear parallel on the graphs indicate that the yaw rate derivatives, Cxr, are not dependent on sideslip angle. Lines that are equally spaced indicate that the sideslip derivatives CxB are not dependent on yaw rate. If the lines are straight, this indicates that the yaw rate derivatives Cxr are independent of yaw rate.

If the lines on the graph cross, this indicates that the sideslip derivative, CxB most likely changes sign with sideslip. The distance between the lines indicates the magnitude of the sideslip derivatives. With these rules we can examine the curve sweep plots.

Figure 21 presents the results for the full configuration. As expected at the low AOA the curves are parallel, equally spaced and nominally straight indicating little cross dependence on yaw rate or sideslip angle. This same pattern holds until about 15 degrees AOAwhere some irregularities can be observed in the roll moment curves. These irregularities are increased at 20 degrees AOA. The roll moment curves are equally spaced and parallel but are not straight. In fact the slope of the lines and hence the roll due to yaw derivative changes sign. At 25 degrees AOA the yaw moment curves start to become closer together indicating a reduction of CnB. The asymmetric effects discussed previously can be observed here also since for positive sideslip the curves are closer together (almost zero for f = - .02) then for negative sideslip. At 30 degrees and small sideslip angles and yaw rates Cn_ is positive. At the larger sideslip angles CnB changes sign for " positive sideslip and is greatly reduced, but still positive for negative sideslip. For this AOA small negative sideslip yields the same positive - CnB for the two lowest yaw rates diminishing to zero at the highest yaw rate.

For small positive sideslip the value of CnB starts positive,goes negative and shifts stronglypositive again as the curvatureincreases. For negative sideslipsabove 5 degrees, CnB is a constant negative value for all yaw rates.

For positive sideslipsabove 5 degrees Cn_ is negativeat the small yaw rates and approacheszero at _ = - .04. In roll for small sideslipangles there is little or no dihedral effect. However at _ degrees sideslip there is a strong dihedral effect which is maintainedfor all yaw rates.

At 35 degreesAOA the yaw moment coefficienthas the followingcharacter- istics. For small positive and negative sideslip CnB remains positivefor all curvatures. For sideslipsabove _ 5 degrees CnB remains negative for all curvatures. In roll the positive 5 degrees sideslipcurve is not parallel to the remainingcurves causing changes in sign in CaB from stable to unstable to and back again at each curvature increment. At 40 degreesAOA the value of CnB is seen to change signs not only between 5 and lO degrees sideslip but also with yaw rate and directionof sideslip. At zero yaw rate CnB based on the + 5 degree sideslip incrementsis positive for positive sideslips (nose in to- ward turn center) and negativefor negative sideslips,i.e. even bistable be- havior. At the incrementsfrom _ 5 to _ lO degrees sideslipthe signs are reversed giving odd bistable behavior. At yaw rates between f = - 0.02 and -0.04 CnB is positive for all positive sideslip angles and negative for all negative sideslip angles. This situationis reversedat yaw rates past = - 0.045. The roll moment shows consistentnegative CnB but with a chang- ing magnitudewith yaw rate. Finallyat 45 degrees AOA the roll moment curves remain in correct sequencewith only the magnitudeof CaB changingwith yaw rate. The yaw moment coefficientexhibits complex behavior. At zero yaw rate CnB is negative or near zero for both directionsof sideslip. At first curvatureCnB becomes uniformlynegative for all sideslipsand re- mains so at the next yaw rate with the exceptionof large negative B for which CnB is slightlypositive. For yaw rates past _ = - 0.045 CnB ex- hibits odd bistablebehavior just the opposite of the situationat 40 de- grees.

Figure 22 presents the same results for the case of the full configur- ation without LEX. Here we will try to highlightthe differences. The differencesat the two lowest AOA are minimal. At 15 degreesAOA the con- figurationwithout the LEX starts to show a significantlyreduced spacing between curves indicatinga reduction in CnB and C_B over the full configur- ation. At 20 degreesAOA the yaw moment curves show irregularbehavior at zero yaw rate and cross with increasingyaw rate. In detail we have at zero yaw rate a positive CnB for small sideslip angles and a negative CnB for large sideslip angles. At f = - 0.03 the situation for large positive sideslip changes sign. For the higher yaw rates the value of CnB becomeseven more negative for negative sideslip. At 25 degreesAOA the above propertiescon- tinue.At30 degreesAOA CnB is positive for negative sideslip at zero yaw rate and is positive for small positive sideslip angles and negative for larger sideslipangles. As the curvatureincreasesCnB becomes negative for positive sideslip. With LEX this trend is reversed at this AOA. For the higher AOA the roll moment is well behaved but the yaw moment shows mixed activity at the low and intermediate curvatures,finally setting on a pattern _ at the higher yaw rates. At 45 degrees this pattern is odd bistable behavior of Cn_ which is the same for the configurationwith the LEX. ._ Figures 23 and 24 present results for the fuselage, wingand horizontal tail with and without the LEX. In both cases the rolling moment is better behaved then in the full configuration with little crossing of curves except at 35 and 40 degrees AOAwith LEX on. Yaw moment curves cross at 40 degrees AOAwith LEX on and 35 degrees with LEX off. The resulting effects are dif- ferent for the two configurations with the configuration with LEX showing weathercock stability at 40 degrees AOA for all curvatures and small sideslip angles with some negative stability at large negative sideslip at intermediate yaw rates. With the LEX off yaw stability virtually disappears at high yaw rates.

As might be expected Figures 25 and 26 for the fuselage, wing and vertical tails show more dramatic results indicating interaction between the vertical tails and the nose or LEX vortices. For AOA of 15 degrees and negative side- slip, nose away from the turn, an interchange of sign in CnB occurs for the large side slip angles and maximumcurvature for the configuration without the LEX. No hint of crossover is exhibited by the vehicle with the LEX. At 20 degrees AOAwithout LEX large sideslip angles greatly reduce the yawing moment and cause CnB to change sign for the larger sideslip angles. The curvature enhances this diminished effectiveness for large negative sideslip angles. Such behavior is not observed in the configuration with the LEX.

At 25 degrees AOAboth configurations show a reduced CnB with the LEX _ the curves basically staying in order. Without the LEX there is a switching in the sign of CnB going from small to large sideslips at all curvatures but a considerable difference in the magnitudes involved with different curvatures.

At 30 degrees AOAthe configuration with LEX keeps the curves in order with little distance between them for both roll and yaw moment. Without LEX the yaw moment displays an even bistable behavior. At the higher AOA the curves are mixed for both configurations in yaw but are well spaced apart for the roll moment.

The Fuselage-Wing-LEX interactions are displayed in Figures 27 and 28.

Most of the activity here occurs at 30-40 degrees AOA. At 30 degrees roll moment is sensitive to sideslip for the configuration without the LEX while it is considerably less sensitive with the LEX in place. The opposite is true in the case of yaw moment.

Figure 29 displays results for the fuselage alone configuration. At 20- 35 degrees A0A the sign of CnB depends upon the sideslip angle at the larger yaw rates. In particular nose in toward the center of the turn is stable while nose out is not. These results are typical of long nosed vehicles.7 The situation returns to normal at 45 degrees AOA.

Figures 30 and 31 show the results of tests on the full configuration with the leading edge flaps up with and without the LEX. Difficulties are first encountered at 15 degrees AOA for the configuration without the LEX and at 20 degrees AOAfor the configuration with the LEX. In both cases a considerable reduction in the sensitivity of yaw moment with respect to sideslip is encountered. For the case of no LEX this condition leads to an odd bistable behavior at 25 degrees AOA. Such a condition does not develop with the LEX on.

Figure 32 shows the effect of trailing edge flaps on the full con- - figuration with LEX. The overall results are similar to those for the full configuration without trailing edge flaps.

The above discussion details the observed effects of curvature on the lateral-directional stability derivatives, The mechanism of the flow field which produces these results has not been discussed since a considerably more _ detailed study of the figures must be made. It is speculated that many of the characteristics observed above are caused by interaction of the nose or LEX vortices interacting with separated flow over the wing and with the two vertical tails. The exact interaction has yet to be determined.

REFERENCES I. AGARD Conference Proceedings No. 235, Dynamic Stability Parameters, November, 1978. _ 2. Chambers, J. R. and Grafton, S. B., Aerodynamic Characteristics of Airplanes of High Angles of Attack," NASATM 74097, December 1977.

3. Grafton, S. B., Chambers, J. R. and Coe, P. L., Jr., "Wind Tunnel Free- Flight Investigation of a Model of a Spin-Resistant Fighter Configur- ation," NASATN D-7716, June 1974.

4. Malcolm, G. N., "New Rotation-Balance Apparatus for Measuring Airplane Spin Aerodynamics in the Wind Tunnel," Journal of Aircraft, Vol. 16, No. 4, April, 1979, pp. 264-268.

5. Queijo, M. J., "Methods of Obtaining Stability Derivatives," NASASP-258, pp. 71-101, 1971.

6. Lutze, F. H., "Curved Flow Wind Tunnel Test of a Spin-Resistant Aircraft Configuration," Dept. of Aerospace and Ocean Engr.Report, VPI-Aero. 067, August 1977.

7. Lutze, F. H., "Experimental Determination of Pure Rotary Stability Derivatives Using a Curved and Rolling Flow Wind Tunnel," AIAA-80-0309, 18th Aerospace Sciences Meeting, Pasadena, Calif.

8. Lutze, F. H., "New Calibration and Corrections for the VPI Stability Wind Tunnel Curved Flow Test Section," Dept. of Aerospace and Ocean Engr. Report VPI-Aero-069, August 1977.

9. Pope, A. and Harper, J., Low Speed Wind Tunnel Testing, John Wiley, 1966.

TABLE 1 Configurations Number Symbol Number Symbol 1 FWVHL 10 FWVL 2 FWVHL ah = - 12 II FWH 3 FWVHL 6f,_e = 0 12 FWV 4 FWVHL af,t e : 20 13 FWL 5 FWVHL ah = - 24 14 FW 6 FWVH 15 F 7 FWVH af'_e = 0 16 FIVVHL ar = 30 8 - 17 FWVHL 6a = 25 9 FWHL 18 FWVHL 6d = I0 where the following symbols are defined F = fuselage W = wing V = vertical fins H = horizontal tail L = leading edge extensions (LEX) ah = horizontal tail deflection (positive trailing edge down) af'_e = wing leading edge flap (nominally down 25 deg.)

af,t e : wing trailing edge flap 6r = rudder deflection (positive trailing edge left) _a = aileron deflection (positive right aileron down = aa) ad = differential tail deflection (positive right horizontal tail down ad / 2) TABLE 2 Model Geometry Reference Geometry Wing Span = 0.798m (2.619 ft.) Wing chord (MAC) = 0.245m (0.805 ft.)

Wing Area : 0.597m (1.960 ft.) Center of Mass = 0.24 MAC Configurations 1,2,3,4,5,16,17,18 6,7 9 Frontal area 0.028m2 (0.300 ft 2) 0.028m2 (0.300 ft 2) 0.028m2 (0.300 ft 2) Planform area 0.322m2 (3.464 ft 2) O.300m 2 (3.234 ft 2) 0.313m2 (3.374 ft 2) Profile area O.120m2 (1.294 ft 2) O.120m 2 (1.294 ft 2) 0.097m2 (1.040 ft 2) Volume O.O13m 3 (0.476 ft 3) O.O13m 3 (0.476 ft 3) 0.013 m3 (0.476 ft 3) Configurations I0 II 12 Frontal area 0.028m2 (0.300 ft 2) 0.028m2 (0.300 ft 2) 0.028m2 (0.300 ft 2) o Planform area 0.284m2 (3.058 ft 2) 0.292m2 (3.144 ft 2) 0.263m2 (2.828 ft 2) Profile area O.120m 2 (1.294 ft 2) 0.097m2 (1.040 ft 2) O.120m 2 (1.294 ft 2) Volume O.O13m 3 (0.476 ft 3) O.O13m 3 (0.476 ft 3) O.O13m 2 (0.476 ft 3) Configurations 13 14 15 Frontal area 0.028m2 (0.300 ft 2) 0.028m2 (0.300 ft 2) O.020m 2 (0.210 ft 2) Planform area 0.276m2 (2.968 ft 2) 0.254m2 (2.738 ft 2) O.l12m2 (1.210 ft 2) Profile area 0.097m2 (1.040 ft 2) 0.097m2 (I.040 ft 2) 0.097m2 (1.040 ft 2) Volume O.O13m 3 (0.476 ft 3) O.O13m 3 (0.476 ft 3) O.O13m 3 (0.459 ft 2) TABLE 3 Curved Flow Parameters Curvature # rb / 2V _P N / m3 (Ibs / ft3) BR L 0 0 0 1 -0.0253 8.771 (0.601) 2 -0.0380 13.835 (0.964) 3 -0.0515 18.242 (1.250) 4 -0.0707 24.226 (I.600) Configurations Shape factors All C1 = 0.O3 C2 = 1.20 C3 = 0.83 Fiaure 1 Curved Flow Test Section

f

1.161m(3,808ft) = 0 .245m(O.8 0 5ft) S = O.182m2(l.960ft 2) Figure 2 Sketch of Basic Model 1.0 0.5 -0.5 -1.0 2.0

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, 8 (deg)

Figure 6 (Continued) 0.q0 0.08 0,20 0,06

Cy o.oo _ - o.ou

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x_

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B (deg)

Figure 6 (Continued) - O. LtO O. 08 0.20 0.06

_'_ '_'-_- o.o _'

Cy o.oo _ _

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;t -o.qo C_ o.oo

o o_ -o02 \k

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- / 9 (de9)

Figure 6 (Co n tinued) O.qO 0.08 0.06 °.2°f_..

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C_ o.oo "__L \,\

-0 . 20

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0.06 -o.oq _ x ,_ O.Oq -0.06 0.02 .._ k,x. -0,08 -10 -5 0 5 10

Cn o oo _'_I__J_-_-''_--

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(!)FWVH -0.0_I z_ FWHL ¢' FWH -0.06 St_b,_yAxes Ctrva{ure 0.0000 -0.08 c_ _q5 0 " -I0 -5 0 5 i0

# (de9)

Figure 6 (Continued)

o .o! 0.0.6 I

o 2or: _ o. o0

%,_ O.Oq

c¥ ooo '__ __ . __

-0 20 O. 02 0 08 -0.02 0 06 - 0, Oq o.oq -o.o6 -0,08 0.02 ____-.... , _ -10 -5 0 5 10 Cn 0 O0 " J • -0,02 (_ - "_ m FWVL ® FWV -0,0u_ _ FWL FW -0,06 . F 5 tabl_L_ t Rxes -0.08 CurvaJcure O, 0000 -10 -5 0 5 10

" / 9 (de9) o c =1.o

Figure 7 Variation of Static Lateral-Directional Characteristics With Angle of Sideslip - Configurations 10,12,13,14,15 o. qo I o 08 I 0 06 _ - °" a °c_,...,

ICy 0.00 _-_.._ _

-0.20 0 02 0,08 -0 02 0.06 -0 04 0. oq I -0 06 I -0 08 1 0.02 5 10

_._ --± _._ -lo -s o

Cn o.oo _._,,_

-o. o2_r' -_" _ [] Fwv

O FWV -0,0q _, FWL _> FW -0.06 + F S [ab,_{y Rxes - 0.08 Curva{ure O . 0000

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#

td J"e 9" _ =s.o

Figure 7 (Continued)

o..o , 008 I

• 0,20 0.06 Cy 0.00 _

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I

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/ _(de9) _ -lo.o

Figure 7 (Continued) 0.40 0.08 0.06 m C¥ 0 O0_ _--4 0 04

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o.oa I _o02

O. 06 -00U i 0.OU , -0 06 --

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_ . - -lO -5 0 5 I0 Cn 0.oo "__'J" B (deg)

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Figure 7 (Continued) 0.40 0.08 0.20 ----- 0,06 -- Cv 0 O0 _- O.OL_ :-_ _, 0.02

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0.08 -0.02 1"<.%

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0,06 -0,04 0,04 -0.06 -o o8 0 02 b"--,

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#

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Figure 7 (Continued) o.qo 0,08 0 20 O. 06 .

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td J"e9" o_ =25.o

Figure 7 (Continued) o.qo 0.08 0.06 -O.Oq O.Oq -0.06 "- -0.08

o. _ "\ -lo -s o s 1o

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#

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Figure 7 (Continued) O,qO I 0.08 0.20 _'-- _xx 0.06

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1"4

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Figure 7 (Continued)

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k

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Figure 7 (Continued) O,qO 0.08 _"" _ 0.06

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"t Figure 7 (Continued) o,qo 0,08 . 0,20_i_ 0,06 (Zy 0 00

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0 02 _ - , [] FWVHL O FWVHL 8h --12" -O.Oq / " FWVHL 8r , ]e- O" 4> FWVHL 8r , _:e- 20" -0.06 . FWVH 6 r , ]e - O" S tabl_t_ t Rxes -0.08 Curva{ . ure 0 , 0000 -i0 -5 0 5 I0 .

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Figure 8 Variation of Static Lateral-Directional. Characteristics With Angle of Sideslip - Configurations 1,2,3,4,7 O.qO 0 08 O, 20 0 06 Cy o.oo _' o oq ---- __'_ %_ 0 02 -0.20 W -0._0 C, 0 O0 _:__ O. 08 -0 02 0.06 -O.Oq O.Oq -0.06 0.02 _ -0.08

A_ _ _ -io -s o s io

__ # (de9)

Cn 0.00 _-_o [] FWVHL

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© FWVHL _h"-12 " -O . Qq _, FWVHL _r , ]e = O " __ 4> FWVHL _ r , {.e = 20" -0.06 @ FWVH 6 r , ]e - O" S _,abl ] l[_ Rxe6 -0. 08 CurvaJcure O. 0000 -10 -5 0 5 I0

/ _ (de9) c_ -s.o

Figure 8 (Continued) 0 40 O.08

o 2o_ o.o6

Cy 0 O0 _ O.Oq -0 20 0.02 __

-o _o C, o.oo _%,_

0 08 -0,02 -_ 0 06 -O,Oq O.Oq -0.06

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On

0.00

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#

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Figure 8 (Continued)

o._o 0.08

0.06 -O.Oq O.Oq -O.Ofi

0.02 __ io -5 o 5 !o

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# (de9] _ =IS.o

Figure 8 (Continued) o.qo 0.08 0,20 0,06

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C¥ o.oo ,,, , __ _..._ k

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Cn o.o "_'---_,_-__ , 8 (de 9)

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td ) - e9" oc -2s . o

Figure 8 (Continued) O.qO 0.08 0.20 0.06 -2 Cy 0.00 _ o.oq

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#

!,a j"ecj' o( - 30.0 Figure 8 (Continued) o.qo 0.08 0.20 0.06 .

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# (de91 c x =35.0

Figure 8 (Continued) 7O 0._o 0.08 0,20 0,06

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Figure 8 (Continued) 0,140 0.08 0 20 L O, 06

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C, o.ool _ _b_ _ tc---""------ " # (deg)

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Figure 8 (Continued) O.qO 0.08 o, 0.20 f _ -._.. 0,06

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# (de 91

Figure 9 Variation of Static Lateral-Directional Characteristics With Angle of Sideslip - Configurations 1,16,17,18 O.qO 0.08 (_" 0.06 o. 2o_-_..

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Cy o.oo _ _._

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# ( d e91

Figure 9 (Continued) O,LtO O,08 ()"" 0.06 o.2o_ _<.....

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Figure 9 (Continued) o.qo 0.08 0.20 I)''- 0.06 C¥ 0 O0 _-_ "_, o.oq

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C__.no.oo J_ f , 8 (deg)

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Figure 9 (Continued) 0.g0 0.06 0.20 _ 0.06 tL )--__

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Figure 9 (Continued) O,qO O,08 0.06 o.2o_ _.....__ _...

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O.08 -0.02 _-__.._k_'- N 0.06 -O.Oq O.Oq -0.06 Figure 9 (Continued)

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# (deg)

Figure 9 (Continued) O.qO 0.08 O. 20(_.. 0.06 "4_ O.OU -0.20 0.02 _n

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Figure 9 (Continued) 8O O.qO 0.08 0.06

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Figure 9 (Continued) O.Oq I 0.02 0 .008 [] FWVHL (D FWVH FWHL 0.006 <> FWH 0.0OLI St,abJ]4_Axes [ Curvature O. 0000

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Figure I0 Variation of Lateral-Directional Static^Stability Derivatives with Angle of Attack, r = 0 O.Oq 0.02 • _._ _.. L,_.,,.

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Figure I0 (Continued) O.Oq 0.02 Cvp O. O0 -0.04 [] FWVHL 0.008 (!)FWVHL _h"-12" __ _' FWVHL 6r , ]e- O" 0.006 4> FWVHL 5r, _.e - 20" __ 4" FWVH 5 r , ]e - O" Fixes 0.00q S {ab,_t._ t [] _._ Cur v ature O. 0000 - --

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Figure I0 (Continued) 0 .04 0.02 - CYB 0.oo

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-0.0q [] FWVHI _ O FWVH 0,008 '_ F WHL FWH O. 006 S L ab,|t.y Axes C u r v at u re -0 . 0253 O.OOq 0.004 0.002

o.ooo \

-o.oo2 __. \ / _ \_ _ . .. -._

} > .

-0.004 \ \ / \ , -0.006 0 5 10 15 20 25 30 35 L _O q5

O ((de91

Figure II Variation of Lateral-Directional Static Stability ^ Derivatives with Angle of Attack, r = - 0.0253 0.04 0.02 - t -0 02 _' _r----_ , .I _ ._.

_ I m I F u lvLI I T I_

-0.04 -- O FWV FWL 0.008 -- <_ FW . F Axe s 0.008 -- S1_bli_ 0.004 -- C u rvature -0.0253

o.oo2 _______ ,. ..__ _

.

-0.002 _r- x, -0.00_ 0.004 0.002 c_ o.ooo _ _____ _ - _._ _:._ _," --_ -,_..

-0 002 -_,,__ _ - _

-o.oo. _, \

-0.006 0 5 10 15 20 25 30 35 qO 45 O( (de9) :Figure II (Continued) 0.04 0.02 ' CYB 0.00

-o.o2 _ "" _ _ _ _ - ___

[] FWVHL

I I I I i I_

-O.O[l 0 FWVHL i_ h --12" A FWVHL _ r ,le - O" 0.008 (> FWVHL _ r , _e - 20" . FWVH 6 r ,le - O" i O. 006 S{ab,i_ t Rxe_ O.OOU , Ya v rat, e -0.0253 I I I I 0.002 ____.. _ _-_ ,,

Cb o . ooo k_ "_ / '_ "7_%_

-o002 \ - "_ "\

• _" -0. OOLI O.OOL] 0 . 002

C_ o.ooo, , <_"

-0.00_ ----" \

\

-0.006 0 5 10 15 20 25 30 35 qO q5

(X Ne9)

Figure ]1 (Continued) O.Oq 0.02 C y_ 0 O0 __---- , _ -- "_'-" -0.02 ° _ _J ' '< '_--- [] FWVHL -O.Oq 0 FWVH ,' , FWHL 0.008 FWH O. 006 5{ .ab,]lt_t Axes -- C urva{ure -0. 0380

o.oo, Ii i i

o 002 __. _ . .._ ___._

Cn B 0.000 i _..

z, . . . ... . . .. - -- ' r''" _.

- - k,,,,,, .... ====4 _::::C '' ' _ _ - - - -- "-""_ ' , - -.,

o_ . -- - -.%

-0.00 " " _ i " - -O.OOq O.OOq 0.002

-o.oo2 _ \ 7 _" _ / _<

-O.OOq \ -[._ f _" "_'" \ " ( -0.006 0 5 10 15 20 25 30 35 qo q5

O( (de 9]

^ Figure 12 Variation of Lateral-Directional Static Stability Derivatives with Angle of Attack, r = - 0.0380 9O 0.0q 0.02

-oo2 I: t _ -_J I, • I I I I < '-.. _

[] FWVL _ / J -0.0q (D FWV FWL 0.008 O FW -. F 0.006 - S_a6,_l_ Rxes C ur v a { ,u r e -0. 0 3 80 O.OOq - _ _ .._I "_]'-.

0 . 002 _- _-_ _b- _ - ._ _

c._ o ooo _>__"_

•

• _- "-,_ -0 0o2_ _\ -0.004 " - O.OOq 0.002

C_ o. ooo __.... /

S

-0.002 \ S ' _ " _ - _ -0.00LI _ _

" " _'-"__ "_ _--<l_ ""

\ > -0.006 ) 0 5 10 15 20 25 3 0 3 5 q5

O ((de91

Figure 12 (Continued) 0.04 0.02 Cy_ 0.00 -0.02 ° I

'' ' ' 'L_

-0.04 m v wv_i O FWVHL 6_--12" 0.008 _ FWVHL _,o le- O" 4> FWVHL _,, te- 20" .

0.006 4" FWVH 6 r . ]e - O" S t . abl]lt , _ / Rxes 0.004 Yav rat.e -0.0380

o ' I =

C nB O. 000 ,, -" _ _._ . ,

-0.002 "_f

-0.004 0.004 0.002 -0.004 _ " -0.006 0 5 10 15 20 25 30 35 40 45

(X (de9)

Figure 12 (Continued) 0.0q 0.02 O.OOq 0.002

-o.oo_ _"_ .... -' _d _ "_ _k '_

_ '/ \ "x3

_ 0 _ OOLt '_' \ "I "'_ --__-, , ....

). . ._.._.4 ) -0.006 0 5 10 15 20 25 30 35 LIO q5

O _( d eS)

Figure 13 Variation of Lateral-Directional Static Stability Derivatives with Angle of Attack, r = - 0.0515 O.OG 0.02 .4 YB O. 00_ _----_ _- _ " "-"------_ _.-._._ _, _0.02(, _ " ,_ ____-_ , , q_-_

i i j___

-O,OU , [] FWVHL (D FWVH 0.008 ' "_ rWHL _> FWH O. 006 St . ab,_} . _Axes -- O. OOq Cor v a_ure -0.0515 --

I

o 002_::_ c_--..._ ,.

\<:_ "

Cn_ 0.000 -_ -'_-_ _.

-0, "'__"- _'_"-k_ --__- "_ -O.OOq O.OOq 0.002 C_ o.ooo _ __ \

-__-_k-.._ -- _ " . __ ,x

-O.OOq \ -_ /!

-0,006 0 5 10 15 20 25 30 35 u,O q5

O ( (de9)

i Figure 12 (Continued) O .OY 0.02

Cy_ o.oo

-0 . 02' _+ _ -_

E] FWVHL L -0.0_ O FWVHL 6h .-12" FWVHL 6 r, ]e - O" 0.008 4> FWVHL 6 , , {e- 20" 1 . FWVH 6 , . l e - O" I 0.006 S t.ab,ld;_ / Axes l 0.0014 Yav rate -0.0515 1

I

o002 __ _. ___

Cn , 0 . 000 k_ x .. _ ( _ . _ . _ __<_ -0 . 002 \ -O.OOq 0.00_ 0.002

, / \ _4

c_ o.ooo , ___, _ .. __ \

-o oo_ -__ / \ /" -'_\

" _ _7

-0.006 0 5 I0 15 20 25 30 35 LIO q5

(X (deS)

Figure 13 (Continued) " • O.Oq 0,02

-o oo c " _" __ _- _ -

- rq FWVHL' _L__ -0.0q (D FWVH FWHL 0.008 _> FWH ___ 5 _ab,lb / Rx e s 0 , 006 Ctrvat, ure -0. 0707"-- O.OOq ' I ' I O.OOq 0.002 C_ o 000'''r'' / _-...

• , 7_-_ -..___ - _\

-o. oo_ "r _..

. _ : .., X

-o.oo. , ,_ /! "\

-0.006 0 S 10 1 5 20 25 30 35 qO q5

CX (de91

Figure 14 Variation of Lateral-Directional Static Stability Derivatives with Anqle of Attack, r = - 0.0707 O.Oq 0.02 b...

i_--_ p-_ __-q __-

-0.02 -,_...

[] FWVL . / -O,OY --

o FWV

, _ FWL 0.008 -- 4> FW . F 0,006 -- S _ab,_yRxes O . OOq -- Cur v al,,ur e -0. 070"# 0.002 E _)_ '- "-H c,,,o.ooo _ ,/-'- /-- _C <::: -0. _==--_ -_r1_ " " " ' \ _ \ -O.OOU "_---_f O.OOq -0.006 0 5 10 15 20 25 30 35 qO tt5

O (( d e9)

Figure 14 (Continued) Z ", 0.04 0.02 CyB o.oo L I i , , [] FWVHL -0.04 0 FWVHL 6h"-12" A FWVHL _ r ,le- O" 0.008 <_ FWVHL 6 r , te - 20" ._.]__ . FWVH _,]e - O" O. 006 5tab,],ty Axes ..,.------4 0.004 Yav rate -0.0707

c.,, oooo '\ / "_C---_

\ /

/

- o . oo \ /

-O.OOq 0.004 0,002

l_ , , / " "_ _ ""

-0.004 _ X _/-/

-0.006 0 5 10 15 20 25 30 35 qO q5

CXCcle 9)

Figure 14 (Continued) o.oq 0.02 -0.04 [] FWVHL 1 0,008 O FWVHL Z -- _ FWVHL 3 0,006 -- S{,abl_t_ Rxes 0.00!4 __ Cur v a{ , u re 0.0000 1 I I l I I )

0.002

CnB o. ooo _"_3-_

.. %, /

-0,002 -O,OOq O.OOq 0,002 - -0.006 0 5 10 15 20 25 80 35 qo q5

C( (de9)

Figure 15 Variation of Lateral-Directional Static Stability Derivatives with Angle of Attack and Sideslip, ^ r = 0 0.0u_ 0.02 -0.0u_ [] FWVH 1 0.008 (!) FWVH 2 ' _ FWVH 3 O. 006 S{,abl]JiQ t Rxes _ 0. 004 Curva{.ure 0. 0000--- ! I I

o.002__ _-.__-_%, / ---._, / _

- 0 . 002 -O.OOq O.OOq 0.002

C_ 0 . ooo / _--_& / _

-0.002 - j ,_\

-O.OOq \ // -0.006 0 5 I0 15 20 25 30 35 LIO 145

O ( (de9)

Figure 15 (Continued) I00 0.0q 0.02 Cy_ 0,00 r ; _ -- k . ,d -0.02 -0.0q rrl FWHL 1 0.008 _ FWHL 2 A FWHL 3 - " " 0.006 S{a6,_t.yAxes - " " C urv a{ ,u r e O. 0000 O.OOq I I I 0.002

Cn_0. ooo . _._

-0.00_ O.OOq 0.002

C_ o.ooo_"

-o 002 "'_

• --, //

-o.oo. _ //

-0.006 0 5 10 1S 20 25 30 35 qO q5

O ((de91

Figure 15 (Continued) I01 0.0_ 0.02

CYB o. oo

-0.02 -o. oq [] FWH 1 0.008 (!)FWH2 FWH 3 0.006 5 } .a b,_b / Rxes O.OOq '- Curv a _ . ure 0.0000" I , 0.002 -0.002 _ -0.00_ O . OOq 0.002 _ 0.000 _ ' _--- " -... ,, -o.oo2 X\ .\ . / , , 4_---_,_ . _.

.o.oo

-0.006 0 5 10 15 20 25 30 35 qO q5

O ((deg)

Figure 15 (Continued) 0.04 0.02

Cy_ o.oo

-0.02 -O.Oq [] FWVL ] • 0.008 0 I-WVL i: I -_ FWVL 3 O. 006 - St. a bl_._ / Fixes O. 0014 Curva{.ure O. 0000

J_ I I I

0.002 _____ -.

C°_ o.ooo _

-0 . 002 x_ -O.OOq O.OOq 0.002 -0.006 0 5 10 15 20 25 3 0 3 5 LtO LI5

0 (.(de9)

Figure 15 (Continued) 1 0 3 O.OLI 0.02 -0. OLI [] FWV 1 O. 008 ® FWV 2 A FWV 3 O. 006 - 5_ . abt]H,y Rxes - 0.004 -- Cur v a[ u r e 0.0000- I 0.002 .._k J3 On , 0 000 _L / "()------_

• ,_ _--__. / -- , --

-0.002 -O.OOg O.OOq

c_ oooo / f_

ooo2 / _

-0.002 _'_" --_

ooo_ "_,_

-0. 006 '_ '- .'x - 0 5 I0 15 20 25 30 35 L1 _,x'x,_o5 O ( (cle9) Figure 15 (Continued) 0, 0 4 0.02 f . _3 -0.02 "_ -0.04 0.008 I I I I I I [] FWL 1 0.006 -O FWL 2 - _' FWL 3 0. 004 St.ab,lty Axes - Ya, rate 0.0000 0.002

I I

Cn_ 0.000

-o.oo2 @_ _ss_,-" _-_ _

J c ;I.,. ,._ -0.004 I 0.004 0.002

C_ .o ooom. _-__

7k " / _/ _L\

ooo2 "h__ /// ! _

-0.004 _ x_ -0.006 " 0 5 10 15 20 25 30 35 40 45

O ( (de9)

Figure 15 (Continued) I05 0.02 CYB o.oo -0.02 -0.04

o.o08 i i I I i I

----ID FWI 0.006 ---(D FW _-A FW3 O. 00q S_b,_ Rxe s I I 0.002 -- Yav mte 0.0000 , , _ Cn B 0 000 , , . r_

-o. oo2 _-_=, ___ "-_ J "_" --_ :j

-O.OOq O.OOq 0.002 C m 0.000 il_._

-o.oo_ -_.! , _-_

-O.OOq d--- - _ \ -0.006 0 5 10 15 20 25 30 q5

(de9)

Figure 15 (Continued) ]06 O.Oq 0.02 O.OOq -0.006 0 5 10 15 20 25 30 35 qo q5

O(CSe 9)

Figure 15 (Continued).

10 7 0.0q 0.02

CyB o.oo

-0.02 _ ' _ '_ -0.04 [] FWVHL 6 r , le - O" 1 0.008 O FWVHL & r , le - 0"2 I A FWVHL & r , ]e - O"3 0.006 5_6,It . y Ax e s O.OOq Yav rate 0.0000 -- i l I

0.002 __ _, , <_\

,k

Cn_o ooo \ - / 2 !_''_l ' _'\

_.. _ ... 1_ i X _'

-o. 002 __,, /

, -,<_

-- 0 i 00_ 0.00_ 0.002 _b.

c_ o.ooo _ W" "_

-o. oo2 " _ _ _t

" 7_ " "-" 4

-o.oou r _\

\

-0.006 I 0 5 10 15 20 25 30 35 L t O

C(Cdegl

Figure 15 (C o ntinued) I08 O.OY 0.02 0.008 0.006 O.OOq

_ " \ / \

o. 002 I_---'_ - - "_ \ ;\ , ____.__

"-_.. / , : ,_,

\ /

I , I , [] FWVH 6 , ,le - 0"1 -O.OOq (D FWVH 6 r , le - 0"2 ". FWVH 6 r , ]e - 0"3 O.OOq S{ab,lB / A xe s 0.002 Yav rat,e 0.0000 _w 0.000

_o.oo / \

-o.004 .,, \ -_- /, ,.--...._ ¢ , _ _, -0.006 0 5 10 15 20 25 30 35 40 q5

O ( (de9)

Figure 15 (Continued) 0.0_ 0.02 C¥_ 0.00 -0.02 -_ -0.0 q [] FWVHL 6 r . te - 20"1 0.008 _ FWVHL 6,, _e - 20" L I , ". FWVHL & r , {e- 20"3 I O.006 5 ta6,_5 / Axes __ O.OOq Yav rate 0.0000 --

ooo2 _._ "_ _c_ €_

Cn, 0 . 000 , ..._ __.____ _-- ._ :_ _ -0.002 -O.OOq O.00q 0 . 002 %

-o. 002 _ _'4_ \'Tr" /

_o . oo " 'I 7 "

-0.006 0 5 10 15 20 25 30 35 qo ' q5 (de9] Figure 15 (Continued) 0.0_ 0.02 -0.04 [] FWVHL 1 0,008 (D FWVHL 2 FWVHL 3 0.006 S{a&_t_ t Axes : ' C_'va_w'e -0. 0253 O.OOq ' ' ' J_

o

-0.002 -0.00_ 0.00_ 0 . 002 I C_ o.ooo _.__ "_..

-o. 002 _.. _ 2 " _,, " , /

-0,00U " -0.006

o 5 _o 15 20 25 30 35 _0 _5

Figure 16 Variation of Lateral-Directional Static Stability Derivatives ^ with Angle of Attack and Sideslip, r = - 0.0253 Ill 0.0q 0.02 -0.0q [] FWVH 1 (!) FWVH 2 0.008 A FWVH 3 O. o06 Bl, ab&!, / Fixes C urva{ure -0. 0253 0.00q _ I l J -0.002 -0.004 0.o0q 0.002 f

o.ooo , / \

N _ / "-__

-o.oo_ _ / -

-0.006 0 5 10 15 20 25 30 35 qO q5

C<_e9)

Figure 16 (Continued) 0.0_ 0.02 -0.0q [] FWHL 1 0.008 (D FWHL2 , ", FWHL 3 0. 006 S{.abl£t . yRxes O , O0 I-] Ctr v a{,ur e -0. 0253 I I I I 0.002 O,OOq o.oo ,

c_ o. ooo i_ //_# _,, "_\

-0. OOq -,,_ / -0.006 0 5 10 15 20 25 30 35 qo q5

O ((de S)

Figure 16 (Continued) ll3 O.Oq 0.02 ° -0.02 -0.0q [] FWH l 0.008 u ) rwH _ _1 I A FWH 3 O. 006 S{ . ab,]J ly Rxes O. 0014 Curva[ure -0. 0253 I I O.OOq 0 . 002 w 0. 000 _

-0.002 \\

-0. OOq / // _

-0.006 :.

0 5 10 15 20 25 30 35 qO q5

O ((de9)

Figure 16_ (Continued) O.Oq 0.02 -0.0 u , E] FWVL 1 0.008 0 FWVL 2 I z_ FWVL 3 O. 006 5t . abl]_t . y Rxes O . OOq Curvature -0.0253

o.oo_ . _ ___ , _

"--4

-0.002 \ /\

-o.ooq

o.oo I - I

0.002 • // _] L J-- , -- 0 002 _ t.. ._

_. ._ . __4_ / _ , \

. " - __ ,

\ \

-O.OOq \ _' -0.006 \ 0 5 10 15 20 25 30 35 qo i_

( X (de9)

Figure 16 (Continued) ll5 O , OL] 0.02 -O.Oq [] FWVI 0.008 O FWV2 FWV 3 O. 006 S_ , abli_ . y Rxes -- O. OOq i _F)..... Curva{,ure -0. 0253

o.oo2 ____ \ _q

Cn_ 0.000 "_r / "_ - L -0.002 -O.OOq 0.004 0.002 C_ 0.000 i/ _"_"

-o.aou _ 71 -

-0.006 0 5 10 15 20 25 30 35 LJO_

( X (de9)

Figure 16. (Continued) 0.04 0 . 02 C Y B °_ -

o.oo ,.., _._ .... r_ ._ ,_

-0,02 -0.0_ O . O08 I I I I I I iPl FWL 1 --- 0.006 O FWL 2 --- FWL 3 --- O.004 5{afl, ltl / Axes 0.002 Yav rate - 0.0253__

I i

Cn_ 0.o00

-o.002 _'_' 4 _ _'"_ I..._

-o.oo. x%___ _ -'_

O.OOq

o.oo_ /_

-o.oo2 " _ _ _\_\

/ , " - O.OOq -0.006 _' ':" 0 5 10 15 20 25 30 35 qO q5

O ((deg)

Figure 16 (Continued) O.Oq 0.02 CYB 0.o0 -0 . 02 -0.0_ [] FWI 0.008 _ FW 3 A FW3 0.006 5_ab,lt_ Axes O.OOq Yav _e -0.0253 --- I

, I I

0.002 -0.002 -0. 001-I O.OOq 0.002 Cw o. ooo _ -_..

-o.oo2 \_ _...._ \

-o.oo_ \__ /- _\ \

-0.006 _..._,__ 0 5 10 15 20 25 30

O _(de9)

Figure 16 (Continued) O.OY 0 . 008 I I I I I I I I --[D F 'I 0 . 006 --C D F2 _A F3 0 . 00q -- 5_,ab&ty R xe s Y av , ' a_ .e - 0.025 3 0.002 - I I I I I I I _t-- - _.,

Cn_ o . ooo __ _"_%_

- 0.002 _r-_ -- -O.OOq O.OOq 0.002 -0.002 - O . OOq -0.006 0 5 10 15 20 25 30 3 5 u,o q5

CZCde 9)

Figure16 (Continued) O.Oq 0.02 -0.04 FWVHL 6r, _ - O" l 0.008 0 FWVHL 6r ,_" O" 2 I A FWVHL 6 r , ]e - O' 3 I i • 0.006 S { a b,lB / R xe _ O . OOq -- Y a v r a t e -0.025 3 ....

i I

o 002 _ __" • . \-,q>, . ,_. Zk, /

c,, o. ooo '_X%, / _,<;_m

_\ d> V / \

-o . oo2 ,_ /

.= -O.OOq 0.00_ 0.002

c_ oooo . 2_\

-ooo2 _ __ ¢ ---..,, ;_,,,, - o . oo_ ,,, ,

\ \/

-0 . 006 0 5 10 15 20 25 3 0 3 5 qO 5

C ¢ ,_ (de9)

Figure 16 (Continued) O.OLI 0.02 - Cy_ o . oo -O.Oq [] FWVH 6r, ] e - 0"I O FWVH 6r,]e - 0" ?

i 0.008 FW.VH 6r,6 - O'3]__ R xe s O. 006 t_ tab,lty Yav r a{ e -0.0253 O.OOq ' ' Cn. o.ooo "_ x_ _ V " \,, -0.002 -O.OOq O.OOq 0.002 CIB 0.0oo L

-o.ooq _ . _ - _ .. .._

( -0.006 0 5 10 15 20 25 3 0 3 5 qO q5

CX: (de9)

Figure 16 (Continued) 0.0_ 0.02

CyB o.oo

- 0 . 0 _ _ " " -o.oq 0.008 [] FWVHL 6 r , te - 20" 1 (D FWVHL & r , {e I 20" 2 , ", FWVHL 5 r , "ke - 20 ' 3 0.006 S L_ b ll_,_ R xe s 0.00q Yav rate -0.0253 o . 002 _._:=q_,.,_ -_. . ..._, ' '"_.o =:4 --_ ,

- x_

-0.002 -O.OOq 0.004 0.002

c_ o.ooo_. __&z / _ _\

L _ -0.004 -_ _ -- - -0.006 ,- 0 5 1 0 15 20 25 30 35 qo q5

O ((de9)

Figure 16 (Continued) O.Oq 0.02 -O.Oq [] FWVHL 1 0 FWVHL 2 0.008 FWVHL 3 5 £ ablU.y Rxes 0.006 C urva{,ure -0. 0380 O. OOL; , I O. 002 _ _--_, ------_._.. _ kJ _r _b-- , ' -0.002 -0 004 I 0 ooq t 0 002

/ \

c_ oooo d___

-o oo_ %_ _- -___

I 1

-0.006 0 5 10 15 20 25 30 35 qO q5

(X ( d e9)

Figure 17 Variation of Lateral-Directional Static Stability^ Derivatives with Angle of Attack and Sideslip, r = - 0.0380 O.Oq 0.02 °4

CYB 0.o0

t I -0.0q I'rl FL ,/ VH ] ® FWVH 2 0,008 ± FWVH 3 S i_bi_i_y Axes 0.006 C mva{,ure -0. 0380 i O.OOq " _qx 0.002 i Y"" _ '\ i X

_.-_-__ r - 1_G_ _ _/ __.%

C n_ o.ooo ""_r--" --_ - - -0.002-" •-0.00_ O.OOq 0,002 ) _

, / \

-o.ooq \ '_/

/

-0.006 • ..

0 5 10 15 20 25 :30 35 qO Lt5

(X (de9)

Fig u re 17 (Co n tinued) 0.0_ 0.02 , -0.02 -O . Oq [] FWHL 1

o.oo8 _ _w,Lz I I

,_ FWHL 3 O, 006 5{.abl_i.y Rxes 0 i 0 0 q C urvat.ure -0. 0380

I i

0,O02 Cb o.ooo .- 4L ,/ k,

o _ _ s

I

-O.OOq O . OOq F,'I /

C_ o ooo I _ /

o. 002 , _ '/ _L!

-0.002 ,_, /_/ \ X

-O.OOq / _ -0.006 x_ 0 5 10 15 20 25 30 35 qO q5

O { (deg)

Figure 17 (Continued) O.Oq I 0.02 _YB O. O0 -0.0 u, 0.008 w r wM ] O FWH 2 0.006 z_ FWH 3 S _,abI_[_ Fixes 0.00q C urva_,ure -0. 0380 I I !

0 . 002

I

-O.OOq O.OOq 0.002 CW 0.000 _--_ -o.002 ._ , ,

-o oo, _ \ _--_

• _--_ ,_ __

-0.006 Ix, / "\

0 5 10 15 20 30 35 qO q5

O _(d, I)

Figure 17 (Continued) :', 126 O.Oq F 0.02 CY B 0.00 -0.02 i _= ___!_l_'_'_ _---_ B ------_-_ _ _ E:_ -O.Oq [] FWVL l 0.008 Q ) FWVL 2 A FWVL 3 0.006 - Slabi_ t Rxes C urva{.ure -0. 0380 O.OOq

I I1 I

0.002_4_ _, -h_#__\

-0.00_ O. OOLI 1 0.002

C_ o.ooo " f /' _-__

-0.002 _l_L _ _ ,,

-e.ooq _ /

- -0.006 0 5 I0 15 20 25 30 35 qO LI5

C( (de9)

Figure 17 (Conti n ued) O.OLt 0,02 \ CYB O. O0

-o.o2_____=Z_ __ _

I I

-0. Oq [] FWV l (Z)FWV 2 O. 008 _ FWV 3 S {.ab,U.yRxes 0.006 C urva {.ure -0. 0380 O.OOq J / J_-.

0.002 / ""_'\ / ._ ,/ _

C nB 0. 000 _ ,_ _:__I_ _ y __. . _ \ -0.002 -0.00_ 0.00_ 0,002 -0. 002 "%_, _-_---_ _ O _ O 0 _

-o . oo -\\i

0 5 i0 15 20 25 30 35 5

O ( (deS)

Figure 17 (Continued) 0 . 04 0.02 -O.Oq

0.008 I I I I I t

-El FWL 1 --- 0,006 -(!) FWL 2 -- -A FWL 3 0. ooq 5 tabt]lt.y Rxes -- 0.002 Yav rate -0.0380 __ I Cn B O. 000

-o. oo21 _ _ =_ ' _ p.. .4'_

-O.OOq O. OOLI 0.002 /

/ "_\

C _ o ooo _ # _- - "_

• A \

-o.ooq x,_ -"1 " -0 . 006 0 5 10 15 20 25 30 35 qO q5

O {(de91

Figure 17 (Continued) 0.0_ 0.02 \ CYB o.oo -0 02 -O.Oq rq F W 1 O. 008 © FW A FW3 O. OOG S{ . a61],L_ t Axes O.OOq Yav rat,e -0.0380 - I 0.002 -O.OOq O.OOq 0.002 C_ 0.000 _k..._

ooo. \ "_k\

"\\

-0.006 \ _ p- _ --4

0 5 10 15 20 25 30 35 qO Lt5

O ((de9)

Figure 17 (Continued) ]30 o.oq 0.02 0.008 , , i , , , , (:_-_. ....__ _m F 1 "_Y'" 0.006 -_) F ?

A F 3 0.004- S'[abli't'sl Ax e s - Yav rate -0. 0380 , ,( y , ,.,... ---"(_,,_ 0.002 /

.j \

Cn B o.ooo __ ...+_+-- -+ _

-o.ooa +, -,,,, -O.OOq " O.OOq 0.002 --_"_ -0.002 _\ \ \ -O.OOq X -0.006 ' 0 5 10 15 20 25 30 35 qo q5

O ((de9)

Figure 17 (Continued) O.Oq 0.02 -0.0q [] FWVHL 6 r , ]e- O'l 0.008 ® FWVHL 6 r , ]e- 0" 2 ,_, FWVHL 6r , ]e- 0" 3 0.006 5tabl_b / Rxes 0.00q Yav rate -0.0380 --

' I

/ ¢- " /

C

-"B o. ooo & _ / J; /

-0.002 "--"-N) -O.OOq O.OOq Figure 17 (Continued) O.Oq 0.02 -o.oq 0.008 0.006

o / \

C b o. ooo --.,, . .. - _ f \

I I I I

-0.002 - [] FWVH 6t , le - 0"1 ® FWVH 6r . le - 0"2 -O.OOq _, FWVH 6r , ]e - 0"3 S _ . alD,_ . _ Flxes O.OOq - - Yav rat . e -0.0380 0.002

o ooo

-o.oo_ +"L_ / _._

:r..--. ---E ',, ,

-o.oo_ i>_, ._

" -0.006 0 5 10 15 20 25 30 35 qo q5

O ((de91

Figure 17 (Continued) O.Oq 0 . 02

Cy_ o.oo

_0.02 I_ . [2 ._. . _----_"_ _ --_ - - "_ _ - o.oq [] FWVHL 6r , {.e - 20" 1 0.008 (!) FWVHL 6 r , t.e - 20" 2 , _ FWVHL 6 r , {.e - 20" 3__ 0.006 i S L ab_t._ / Axes O,OOq Ya v raf .e -0 .0380 -

' I I

o.oo2 __ ,,%, _

C n_ o. ooo _" "_,_

,,q

-0.002 -O.0Oq O.OOq I 0.002 C_ o. ooo _,._, / __,.

-0.002 "_ _ / \ \_

-O.OOq "E_ -0.006 0 5 10 15 20 25 30 35 qo q5 O ( Cd e €:::j) Figure 17 (Continued) O,Obl 0.02 -0.04 [] FWVHL 1 0.008 _ rwvmL , " A FWVHL 3 0,006 S[ab1_[y Rxes 0 . 00q Curvature -0,05 15 __ I I l I o.oo2 _, ,__ q_ _ __ ,,

X

-0.002 /

-0.004

o.oou _I

o // "

-0.002 ___ /jr/ _

-o.oo_ _

-0.006 0 5 10 15 20 25 30 35 LIO t15

O ( Ue9)

Figure 18 Variation of Lateral-Directional Static Stability Derivatives with Angle of Attack and Sideslip, r = - 0.0515

o _ _ - J-q-- V-V

0,02 -0.0Lt [] FWVH 1 ® F\ 4 VH 2 0.008 ,,, FWVH 3 0.006 C urva{ure -0.05!5 O . OOq 0,002 Cn_ 0.000 -0.002 - -O.OOq O. OOq _ _ _ _ 0.002_

C_ o.ooo+

_ o . oo

-0.00G _ L_ - " 0 5 10 15 20 25 30 35 q0 145

O ( (de 9)

Figure 18 (Continued) O.Oq 0.02 -O.Oq [] FWHL ] 0.008 0 FWHL 2 I FWHL 3 O.OOG S_ab,_y Rxes O. 0014 Curva{ure -0.05 15 I 0.002 CnB o.ooo

__-_ _ "%__ > _

oo _._ ×___

-O.OOq

o.oo. / iX

0.002 //

C_ o ooo I_ / _ _

• --_q. _ "_ "\\

\\

-o.oo_ _k I_ " \

-o.oo

,- -0.006 0 5 10 15 20 25 30 35 qO q5

O (Neg)

Figure 18 (Continued) ]37 0 .Oq I 0.02 -0.02 -O.Oq 0. 008 [] FWH 1 O FWH 2 , ", FWH 3 0.006 5 { . abl_t . yRxes O. 004 Curva{ure -0,05 15 I I 0.002

o

-O.OOq O.OOq 0.002 C W 0 000 _ . --_.., "_",,,+ +._ i_) -o. oo_ _,.. - ,. _...

-0.006 - - 0 5 10 15 20 25 30 35 LtO q5

C_(cle 9)

Figure 18 .(Continued) O.Oq 0.02

C¥_ o.oo

-0.02 ° _ r_ _ _ -O.Oq [] FWVL 1 O I 0 0 8 _ _ W V m Z _ I I A FWVL 3 0.006 S_abi_[¥ Rxes O. OOq Curva[ure -0.0515- . -

I I '

o.002 __ \ _>__4 / __

CnB o ooo _ \x_

• _

-0.002 _ / -O.OOq

I I

0.002

C_ o.ooo ./ 4_

",,,.

-o oo "_ _ y _. _ /

-O.OOq

_o I I .006

0 5 10 15 20 25 30 35 qo LI5

(9((de9)

Figure 18 (Continued)

oo, I i

0.02

-o.o21 _':_'- _'_ _,_ _ , __ 4 _.--- .,4 _ --4Q ...-4 _.._\_f

-0.0q [] FWV 1 0 FWV 2 0.008 A FWV 3 5 _abii_) t Rxes 0.006 - C urva {.ure -0.0515-

I '

o.oo

o002 _ __ --__--_----_

c._ o.ooo "_..... /, , __

-0.002 -O.OOq O.OOq 0.002 / _ 1 .. _

C_ o.ooo jr- _\

-0.002 _ --_ , ,-...... ----i:

-o.oo<i \ X

'\x , x_ \

-0.006 0 5 10 15 20 25 30 35 \ q5

\

(7,_ (de9)

Figure 18 (continued) O.Oq 0.02

C

- Y# O. 0 O [ o-r'_

•--__

-0.02 -0, OLt 0.008 i i w I I I [] FWL1 0. 006 O FWL 2 -- A FW L 3 0.00q S {.a6,_{._ / Axes -- Ya v rat.e -0,0515 O , 002

I I I I

Cn_ 0.000

-o.oo , _ /, /

-o . oo, _'- _ //>_

0.00q 0.002

C_ o.ooo _'- _ // \"

/ ¢_ N _\

-O.OOq -0,006 " 0 5 10 15 20 25 30 :95 qo q5

( X (de91

Figure 18 (Continued) O,Oq 0.02 - 0.02 -o . oq F1 FW 1 0.008 (D FW 2 z_ FW 3 0. 006 S{,abl_{._ / Rxes _.---_ 0,00q Yaw rate -0,0515 I 0.002 -O.OOq O.OOq 0.002 CIB 0.000 _---- ' _

-o. 002 - _,_......._ --._ ___-_

-O.OOq \ _ -0.006 0 5 10 15 20 25 30 35 qo q5

O ((de9)

Figure 18 (Continued) 0.0q 0.02 I I I I ! /

o. 008 _n _- I "_-,. /

-mF2 - (

0 , 006 -- A F3 0.00q -- S_abJ_y Rxes

/ \

-- Yav rate -0.0515 - _ " \

0 . 002 / i "_

/ / [ 1._ Cn_ o . ooo _ -- _" .4r" "_" "<J_.

-0 002 F--_ f

\ t

-O.OOq '- O.OOq

o. 002 - "__"

_--4Y" , . / _ / _ _ O.O00E_----_ ,_----i_- []__-----t_ -O, 002 t_ \\ '

-o.oo4 \

\

-0.006 0 5 10 15 20 25 30 35 qo q5

O ((de9)

Figure 1 8 (Continued) 0.0q 0.02

r-' -

-0.0q [] FWVHL 6,,le- 0"1 0.008 _ FWVHL _r, ]e- 0"2 FWVHL 6r. le- 0"3 O. 006 5"t,ab_]l L _ Rxes 0.004 Ya v rate -0.051.5 0.00q o.oo2 _L.

C_, o.ooo ' _ _" '

• -_.._, /, _,,,_... .

-o. oou \-_

\ X

-0.006 " " 0 5 10 15 20 25 30 35 q5

O ((de9)

Figure 18 (Continued) _D 0.0_ 0.02 -0.04 [] FWVH 6r , ]e - O'l 0,008 _u rwvrl _r, _ " u /4 FWVH 6r , ]e I O" 3 0 . 006 St.abl_{ y Axe s - Yav rate -0.0515 _

o.oo, I, L

0,002 _ / \

C

n , o. ooo "_ "

_ / x3

- 0 . 002 -O.OOq O.OOq 0.002 CW 0.000 -0. 002 _--_ . .-- , _]_-.,.___ __._ /

-o.oou kk_ /

-0.006 0 5 10 15 20 25 30 35 q0 q5

O( (de 9)

Figure 18 (Continued) O.Oq 0.02

CyB o.oo

_0.02 I " -.

-0.0Y [] FWVHL & r , {e - 20"1 0. 008 (D FWVHL 6r , te I ZU _ FWVHL S t , te- 20" 0. 006 £t, ab(_t+y Rxes 0,004 Y aw rate -0,051_5 _ i i I I I

o.oo2 _ r+.._+ ,_::+_...,,_

q

Cn , 0 O00 _"f _ - ] --_------,

• \-_ ____

-0.002 -0.004 0.00_ \

o oo2 / \

/ \

o ooo . \

- O.OOU - "

\ /

\ /

-0.006 " " - 0 5 10 15 20 25 30 95 q5

O ((de9)

Figure 18 (Continued) 0.04 -0.04 [] FWVHL 1 0.008 ® FWVHL 2 A FWVHL 3 0.006 S_ab,_t_ Rxes O. 0014 Corva_.ure -0. 0707 I I I J4k,

o.002 _________

C

n_ o. ooo \

-0.002 -0.004 O.OOq 0.. 002 /

oooo

-o.oo, . -0.006 0 5 10 15 20 25 30 35 qO q5

(X (deS)

Figure Ig Variation of Lateral-Directional Static Stability Derivatives ^ with Angle of Attack and Sideslip, r = - 0.0707 0.0_ 0,02 CyB o.0o _0. 021_P_='_: #_,--__ ,. ,,____q__r-s:_ _"_ ,I, -O.Oq [] FWVH 1 0.008 _ rwvn / --I I A FWVH 3 0.006 ' S_ab,_ Axes O. 004 Curva{,ure -0,0707

o.oo_ _-__ _--_, / _\ 4_ -

On , oooo _ r __ / _

• __

-0.002

-O.OOq O.OOq 0.002 -0.006 0 5 10 15 20 25 30 35 qO q5

O ( (de9)

Figure 19 (Continued) O . OL_ 0.02 J ' t • -0.02 -O.Oq 0.008 , .....

[] FWHL 1 0.006 O FWHL_.

FWHL 3 0.00q 5ta6,1_t.y Rxes C urva{.ure -0.0- / 07 0.002 O.OOq I 0.002 c_,oooo I_-- / _---_,

• - , <

_o.oo_ _q,_ Y_" \', \ x

-o.oou _<..., /i/i \ _, . -0.006 0 5 10 15 20 25 30 35 q0 q5

O ( (de 9)

Figure 19 (Continued) 0.0q 0.02 0.008 [] FWH l © FWH 2 0.006 -_ FWH 3 5 tab,_t_ Axes 0.00_ C _valure -0. 0707 0.002 . J

_n. 2_ ___ _ _ _ ' __ "e

u O0 - -O.OOq O.OOU 0.002 CW 0.000 _"-

-o.oo2 "_ ! _

-o.oo_ \ / . <_

-o.oos x ,f "

0 5 10 15 20 25 30 35 qO US

O ((de9)

Figure 19 (C o ntinu e d) 0,0q 0.02 CYB O.O0 i

-o. o21 _ __-_r" _-_:=_ _-_--{_

-0.0q [] FWVL 1

o.oo8 _ _wv_ z I I

-_ FWVL 3 0. 006 - 5t,abl}t,_ t Rxes 0 . 00q _ Cur v a{. u re - 0. 0707 _ I I I

o.oo2____-____

"'"<U "" _Z---_

Cn_o. ooo _\ "-._

-0.002 ' /

\ /

-0.00q 0.00q

0.002 / \

/ , C_ o.ooo J_k )_

&_ r - \ -0.00q -0.006 0 5 10 15 20 25 30 35 q0 q5

(X(de9)

Figure 19 (Continued) o.oq 0,02

Cy_ o.oo

-0.02 __ :2, • - , _ -- [ ] 4t_'_'_4_'-----_

I i

-0. Oq [] FWV 1 ® FWV 2 0.000 ,_, rwv a S _.abll_._ / Axes 0.006 Curva{.ure -0. 0707

o.oo. I / \

/ \

L_ -0.002 -0.00q O.OOq I 0.002

oooo

-0. OOLI '_'----- I- -\ _ "'--,z ,,,, h -0.006 0 5 10 15 20 25 30 35 qO q5

O (Cole 9)

Figure 19 (Continued) 0.0Y 0.02 Cy_ 0 001_ _ _ _ _=-- " -0.02 -0 , 0 L I 0.008 I I I I I I --rq FWL l 0.006--(D FWL 2 __A FWL 3 O. OOq --- St.abl_t , y Rxes Ya v rat . e -0.0707 0.002 --- Cn_ 0.000

-o. ___'_"_'_ _-

-0004 __r ' _

o. oo2 )_,,

C_ o. ooo t_ _ / _"_

-o.002 "'%_ €'/ \ "\_ \

r

_ _ -- \ "\\

" 1

-000q _ _ / " -0.006 0 5 10 15 20 25 30 35 qo q5

(X (tie9)

Figure 19 (Continued) O.Oq 0 . 02 -O.Oq

o.oo8 I I I I I I

---o FW 1 0. 006 - O FW 2 --_- A FW 3 O. OOq -- S_.abl_._ Rx e s Yav ra_. e -0. 0707 0.002 --

'1

Cn B o . ooo _ J_"_ -0.002 , _-' -- " "=_ _ d" -O.OO q O.OOq 0.002 Cw o.ooo!_ -'-_

-o . oo2 _ _..__.. _

-O . OOq _ _-- _ _._ _ - _ _,_ _---- -0.006 0 5 10 15 20 25 30 35 qo q5

O ( (de9)

Figure 19 (Continued) 0.02 O.OOq 0.002

C_, o. ooo1 _-__ _.__+ _ - :f "-" "<r,,.,, / '

-0. 002 \ i \\

_q 3

-O.OOq \ \

h

-0.006 0 5 10 15 20 25 30 35 qo q5

,. O ((de9)

Figure 19 (Continued) O.O q 0.02

CyB o.oo _

-0.0 q [] FWVHL 6 r , le- O'l 0.008 (D FWVHL 6r, ]e - O'2 • , " , FWVHL 6 r , ]e- 0"3"-- O, 006 5{abt]mt._ R xes __ O'OOL J Yav rat e -0,070" / x ," fi) ' (

o 002 __, _

. ,..,,.,._ _-- . --,

• -_

Cn_oooo / ', "

N r

J

ooo \ /

E_ -O.OOq O.OOq 0.002 G&

C_ o.ooo __ /

-o 002 - _ __ _ • \ _ /. .._,

-.,q y ,£ / _ -

-o . oo_ _, ",.i i \

-0.006 0 5 10 15 20 25 3 0 3 5 qO

C < (de9)

Figure 19 (Continued) O.Otl 0.02 -0.0q [] FWVH 6r , ]e - O'I 0.008 O FWVH 6_ I _ I Ol _ A FWVH 6,,]e - 0"3 0.006 S _ a biIB / Fi x e s (D 1 \ 0.00q Yav rak e -0.0707 // \

\

I I !

\

-.,_

Cn_ O . 000 "_ j.._-----_S" \ -0.002 -O.OOq O.OOq 0.002 _ 0.000

_o.oo

-o.oo

- -0.006 0 5 I0 15 20 30 35 qO q5

O ( L )

Figure 19 (C o ntinued) O.Oq 0.02

CyB o.oo

- 02 _ =" _ "_ O.

-0.04 [] FWVHL 6 r , t.e- 20"1 0,008 (9 FWVHL 5 r , _e - 20_ FWVHL _r ' {.e - 203 O. 006 St .a b],b / Rxes __ O.OOq Ya v rate -0.0707 -- I

0.002 ;_ _ _,_

-0 . 002 - O.OOq O.OOq 0,002 _;)

_ / \

C_ o.ooo_o / \\_k /' \

__ !/ __ / \

-o.oo2 _. ,, _ / / / _- _\ .

-o.oou _ \ /

-0.006 0 5 10 15 20 25 9 0 35 qO q5

O ((degl

Figure 19 (Continued) 0.0bt 0.02 -O.Oq 0.008 , ....

[] FWVHL O FWVH 0.006 -- -- _A FWVH _ r ,]e - 0"_ O.OOq _ Body Rxes _ C u rva{ure 0

o 002 __ __

•

Cn_ 0.000 \ _-.

-0.002 \ N N -O.OOq O.OOq 0.002 - -0.006 0 5 lO 15 20 25 30 35 qo q5

O ( ( d e9)

Figure 20 Variation of Lateral-Directional Static Stability Derivatives with Angle of Attack, Body Axes 15 q o.oq I 0.02 -0.02 I -O.Oq Figure 20 (Continued) O.Oq I 0.02 O.OOq I 0.002 I_ 0.000 & _'_ ____-----'_-----_

-o.oo2 -__ {

-O.OOq \ -0.006 0 5 10 15 20 25 30 35 qO q5

( X (de9)

Figure 20 (Continued)

oo_ I

0.02 -O.Oq 0 I 0 0 8 ' ......

[] FWVHL 0.006 © FWVHL _r. ]e- O" '_' FWVHL 6r , te o 20 " O.OOq Body Axes Curvature 0 C n_ 0.000 _ _k_'_

_o.oo_ _ -_-_<_--_

\

-O.OOq O.OOq I

o . oo_ j_

/ C@ oooo- _,_. / / _"_ ------ z "(_ , / / ' _ . _

_o.oo_ ___ // _ _ /

_::::_ { \_- - -- -

-O.OOq -0.006 0 5 10 15 20 25 30 35 qO q5

O ((de9)

Figure 20 (Continued) 0.04 0.02

Cy_ o.oo

-0.02 _ ] -0.04 0.008 I , , , , , , _El FWVHL 0.006 _(!) FWVHL &h" -12" _ _A FWVHL 6_ = - 2_r I __ 0 i 0 0 _ -- Body Axes _ C ur v a{.ure 0

o

-O.OOU 0.00_ 0.002 - -0.006 0 5 10 15 20 25 30 35 tt0 45

CXNe9)

Figure 20 (Continued)

0.04 I !

0,02 I

!

Cy_ o.oo -0.02 "_ _ -0.04 0.008 30" [] FWVHL '6,- O FWVHL 6,- 25" 0.006 z_ FWVHL 6 o- 10" O . OOLI Bo d y Rxes Curva{ure 0

C

-0.002 "_ _'__ _------

-0.00_ O.OOg 0.002 C _ 0.000

-0.002 ,_ . _ _y

-0.004 -0.006 I _ 0 5 i0 15 20 25 30 35 40 45

(X (de 9)

Figure 20 (Continued) 0.q0 0.I0 0.08 g

o. 20 _ _---m-i_--_

3------e- --_ O-----_D 0.06 C y o. oo =_---- ---_-- _--__ _-- -_ 14 0.0_ -0.20 -O.qO 0.02 I m l-r 17 iF l

C ! _ _ _

0 10 ] 0 00_ _ _ !

0.08 -0.02 0.06 -O.Oq O . Oq -0.06 ..4_--_ ._> i _-- -0 08 0.02 _.-- _.___ / _ n -0. i0 ...I_ _-- _-'"'- 0 -01 oq -0.08

/ '_ rb / 2V

-o. 02 _"

-o.oq []# =-io.o

® # -- -5.o

o -0.06 '_" # =0.0 a

_># =s.o

[]

-o.o8 . B =lo.o

FWVHL ill -0.10 oc -1.0 0 -O.Oq -0.08 _ rB / 2V Figure 21 Variation of Static Lateral-Directional Stability Derivatives with Yaw Rates, Configuration 1 0.40 0.i0 0.06 -0.04 0.04 -0.06 o.o2 , _ - j _,_ _. .. j . 4_ - -_-__- - A--- _ -0.08 _r_ _ -0.i0

C n o. oo_"I " _'- - ___ _

_"_'_4_ "IEt'_-_ 0 -0.04 -0.08

_...___.---48" rb / 2V

-0.02 II

-o.o4 [] # =-lo.o

u

® # ---s.o

m -0.06 ,a / _ =0.0 m

_># --s.o

n

-a.ae . # =lo.a

FWVHL g -0. I0 _ =5.0 0 -0.04 -0.08 rb / 2 V _-.

Figure 21 (Continued) 0.40 0.i0 I " 0.20[] _ ,3 i r] 0.08 _¥ 0.00 ,.. _ 5 i ' 0.06 O, 20 _'-"--'_--_'_'' -@ 0 Obi -o,qo 0.02 _--__m,, E q [] _ _ - .e)_ ___- _ 9 -- _ ,__() o.io C_ o.oo ._..

O. 08 -0.02 _ v --_....9___ _ 0.06 -O.Oq O.Oq -0.06 ._-4'---'i .,-.--, , _ O. 02 I-_-. ' ._ 0 -0 08 _ • 3_ Cn 0.o0 -0 I0 :y_i _ 0 -0, oq -0.08

-o. 02 r"1"_ rb / 2V

-o.oq [] # =-io.o

® B :-5.o

o -0.06 ,x _ =0.0 m

m # --s.o

i

-0.08 .m # --io.o

FWVHI_.

i -0.i0 (x =i0.0 0 -O.Oq -0.08

rb / 2V

Figure 21 (Continued) O.qO 0.10 0.20 n = ] _o_--__ D HO 0.08 I Cy 0.00 , _ -_ _ _ 00G v -0.20 _-'--_-e"--@ 00q -0 qO 0 0 o.io L_ 0 00 _ x O. 08 -0 02 _- O. 06 -0 oq o

-o oq [] # =-1o.o

u

® # =-s.o

a -0 06 ,_,_ =0.0 a

_># =s.o

u

-o 08 . # =1o.o

FWVHL n -0 10 o( =15.0 0 -0. oq -0.08

rb / 2V

Figure 21 (Continued) 0.N0 I 0.i0 O.OLI -0.06 _ '/ -0.08 0.02 _e_ --_ _-_ _'_ _y Jl -0 I0 En 0.0o _---,5"- - _"_ )-"- _ 0 -00q -0 08 ,,,,_ _ " •

L...--4a " rb / 2V

-0.02 o

-o.o_ []# =-io.o

a

# =-5.0

o

-o.o6 _ # =0.o

o

# :s.o

a

-0.08 . # =lo.o

• FWVHL u -0.I0 _ :20.0 0 -O.Oq -0.08

rb / 2V

Figure 21 (Continued) 0.q0 0.10 0.20 0.08 _ _ q r7

' ® c D --()

C

Y O.O0 _----__- --_-- , ,__-- _ O.Off -0.20 O.Oq -0._0 0.02 [] . 9--_ 9 F O. i0 "-'l 0.00 "- _.--_---__...._ __._.-_<_" O.08 -0.02 _-- 0.06 -o.oq O.OLI -0.06

0.02 -0.08

On

o.oo _ ___ - -o. io I, =i_,--- 0 -0. Oq -0.08 J

rb / 2V

-0.02

-o.oLi [] / 7 :-lo.o

I

® # :-s.o

I

-0.06 , _ # :o.o

_> / 7 --s.o "

= 0.08 . / 7 :lo.o "

FWVHL a -0.I0 c( =25.0 0 -O.Oq -0.08

rb / 2V

Figure 21 (Continued) O. L_O O. I0 0.20 0.08 [] 7 ,1 nn

c

0.06 --v 0.00 _ _--_ --_

- k

r v- -0.20 O.Og -0. qO O.02 _ i_ __ ]

o Io C , o oo_--''_ "_J_-

• • _ _ .. _-

0.08 -0.02 0.06 -O.Og O.Og -0.06

-o 08

o.o •

-0. i0

Cn o.oo t_f 4 f 5_'_-

0 -O.Og -0.08

-o.o2 rb / 2V

a

-o.o_ [] / _ =-io.o

a

m / _ :-s.o

-0.o6 "' B =o.o m

m _ =s.o

is

-0.08 . B = ;o.o

,, FWVHL a -0.10 _ =30.0 0 -O.Og -0.08

_ rb / 2V

Figure 21 (Continued) O.qO 0.10 0.20 0.08 I q - --__.4:_- L--E-- "r'l rq -_ ® C _-- ---(9 Cy 0.00 , .,, _ ,_ ,, 0.06 -0.20 "-_"_ O.Oq -- 11--[9-- -0. u , O 0 02 -Fq-_.._ • E..

o.lo C_ o.oo _-_'_-- _._. . 4_-_ _

0,08 -0.02 f 0.06 -0.0q 00q -0.06

oo2 - __ -o.o8

. m>---_. -_

Cn ooo!_ _-_ -

__'-,,_"_ -0"100 -O.Oq -0.08

-o 02 rb l 2V

-o ou []# :-Io.o"

® ,8 =-s.o "

-o 06 , _ , 8 =o.o "

_> _ =5.0 "

-o o8 . ,8 =1o.o •

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