1、NASA TECHNI$-AL MEMORAND I -;.-:+- * - 1 +J?ME TRANSONIC AND SUPERSONIC DYNAMIC STABWTY CWmERISTlCS OF A VARIABLE-SWEEP-WING TACTICAL FIGHTER MODEL Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Report No 2 Government Access108 No 3 Rcctpcents Galal
2、og No SOME TRANSONTC HkRs“LCTERISTT configuration B, 0.9699 meter Rolling moment rolling-moment coefficient, (see fig. 1) qmsb Cl;. = - per radian CL = 3 per radian P a 2 c2 eos a! 4- ls. G P 2; effective-dihedral parameter, per radian pitching-moment coefficient, Pitching moment q ,sc (see fig, 1)
3、Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- acm C,q - per radian a Cmq + C, a - damping-in-pitch parameter, per radian per radian Cma = - aa! 2 Cma - k Cm4 oscillatory-longitudinal-stability parameter, per radian per radian Cmh = a (g) Yawing mo
4、ment yawing-moment coefficient, (see fig. 1) q,Sb per radian Cnr = - Cnr - Cna cos a damping-in-yaw parameter, per radian P = 5 per radian Cn ag 2 CnP cos a + k Cni. oscillatory-directional-stability parameter, per radian - c reference chord (mean aerodynamic chord): configuration A, 0.1253 meter; c
5、onfiguration B, 0.1219 meter f frequency of oscillation, hertz it horizontal-tail incidence angle, degrees Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-reduced-frequency parameter, in pitch, in yaw 2v 2v free-stream Mach number angular velocity of
6、 model about body Y-axis, rad/sec (see fig. 1) free-stream dynamic pressure, /rn angular velocity of model about body Z-axis, rad/sec (see fig. 1) reference area (wing area): configuration A, 0.1009 meter2; configuration B, 0.1055 meter2 free-stream velocity, m/sec body system of axes (see fig. 1) a
7、ngle of attack, degrees or radians; mean angle of attack, degrees (see fig. 1) angle of sideslip, degrees or radians; mean angle of sideslip, degrees (see fig. 1) leading-edge sweep angle of outboard wing panel, degrees angular velocity, 27rf, rad/sec A dot over a quantity denotes the first derivati
8、ve with respect to time. The expres- sion cos a appears in the lateral parameters because these parameters are expressed in the body system of axes. APPARATUS Configurations The two configurations used for this investigation are similar to those used for the static-stability investigations reported
9、in references 1 to 4, except for aft fuselage modi- fications necessary for sting clearance. The more important design dimensions of the configurations are given in figure 2 with additional details given in table I. As previously mentioned, the land-based configuration is designated herein as config
10、uration A. Config- uration B, the carrier-based configuration, has extended wing tips and a shortened Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-fuselage, The configurations have wings at an incidence mgle of I“ with respect to the body referenc
11、e axis and have an inboard sweptback wing-chord eAcidension, or glove, wlzich provides a conventional swept wing when , = - -2 kY)wind on - (y)wind off q $c and the oscillatory-longitudinal-stability parameter was computed as Since the wind-off value of Cy is not a function of oscillation frequency,
12、 it is determined at the frequency of wind-off velocity resonance because Cy can be deter- mined most accurately at this frequency. The wind-off value of Ky - 1yw2 is deter- 2 mined at the same frequency as the wind-on value of Ky - lyw , since this parameter is a function of frequency. For the yawi
13、ng tests, measurements are made of the amplitude of the torque required to oscillate the model in yaw TZ, the amplitude of the angular displacement in yaw of the model with respect to the sting q9 the phase angle X between TZ and qlr, and the angular velocity of the forced oscillation w. The viscous
14、-damping coefficient in yaw CZ for this single-degree-of-freedom system is computed as TZ sin h Cz= and the spring-inertia parameter in yaw is computed as 21 cos X KZ - w = where Kz is the torsiond-spring coefficient of the system and PZ is the moment of inertia sf the system about the body Z-axis,
15、Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-For these tests, the damping-in-gzw parameter was conputed as C,. - Cnj eos a = - - and the oscillatory-directional-stability parameter was computed as The wind-off value of CZ is determined at the freq
16、uency of wind-off velocity resonance, and the wind-off and wind-on values of KZ - u are determined at the same frequency. During the yawing-oscillation tests, measurements were made of the amplitude of the rolling torque TX induced by the yawing oscillation and the phase angle y between Tx and the y
17、awing displacement 9. That part of the induced rolling torque in phase with yawing displacement was used to compute the following expression for effective-dihedral parameter: 2 T cos y T cosy C cosa!+kC =- I6 1: qWSb I )windon-( x9 )wind04 TX cos y The wind-off and wind-on values of 9 are determined
18、 at the same frequency. TESTS The dynamic stability parameters in pitch were measured through a range of angle of attack with the model oscillating in pitch about the body Y-axis. The oscillation bal- ance was rolled 90 within the model to provide oscillations in yaw about the body Z-=is as the mode
19、l was tested through a range of angle of attack. The tests were made at Mach numbers from 0.40 to 2.50 at an amplitude of about 1.1 by using a small-amplitude forced-oscillation mechanism. Reynolds number was constant at about 10,6 X lo6 per meter at Mach numbers from 0.40 to 1,20 and varied from 5.
20、3 X lo6 to 6.0 X lo6 per meter at the higher Mach numbers, The angle of attack was varied from about -5 to 17“. The reduced-frequency parameter was varied from 0,0034 to 0,0250 in pitch and from 0,0181 to 0,1144 in ya-iv, Provided by IHSNot for ResaleNo reproduction or networking permitted without l
21、icense from IHS-,-,-o)l .= v rro pasq, -BTX ;- - - - - 30P SZL paAortra.1 I!e+ Ie+uoz!aoH 02 1 080 30 921 1 a;sea 090 0 30s 0 OZ a!setf :soiloj se s! salqzq pue san3g ayq u! qp ay? 30 uolJeao1 ayL *urxoj xepqzq u! paquasad an eqep ayq 30 lp uo!?:ppz UI TI oq g saxarj u! Illzalydz.13 paquasaxd aJe uo
22、ge8saaul sly? 3ulxnp pau!eqqo zqep ay;C 6 aauaxaja 30 poyqaur ay? 3ursn Ilq palndmoa axad uolqzaol pue azls ssauyBnox ayL esuo!ulqmo;, sno!.mn u panourax Tleq 1quozljroy puz an013 BUM %UM ayl ygM ap-eur axaM spa? Buly?.!d auras o- pue o- 30 sT.uz aauapJ3uI lea -1e)uozJJoq qqyr ah% pue %u$ and Wassum
23、, Donald L.: Supersonic Investigation of the Static Stability, Performance, and Control of a Variable-Sweep Tactical Fighter Model - Phase 2. NASA TM X-1046, 1965. 5. Mechtly, E. A.: The International System of Units - Physical Constants and Conver- sion Factors ( Wiley, Harleth G.; and Lee, Cullen
24、Q.: A Rigidly Forced Oscilla- tion System for Measuring Dynamic-Stability Parameters in Transonic and Super - sonic Wind Tunnels. NASA TN D-1231, 1962. (Supersedes NACA RM L58A28.) 7. Schaefer, William T., Jr.: Characteristics of Major Active Wind Tunnels at the Langley Research Center. NASA TM X-11
25、30, 1965. 8. Wright, Bruce R.; and Kilgore, Robert A.: Aerodynamic Damping and Oscillatory Stability in Pitch and Yaw of Gemini Configurations at Mach Numbers From 0.50 to 4.63. NASA TN D-3334, 1966. 9. Braslow, Albert L.; and Knox, Eugene C.: Simplified Method for Determination of Critical Height o
26、f Distributed Roughness Particles for Boundary-Layer Transition at Mach Numbers From 0 to 5. NACA TN 4363, 1958. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE I . . GEOMETRIC CWAIZACTEMSTICS OF CONFIGURATIONS General Oscillation centers: 0.30
27、E, distance from nose of model. meter 0.40E, distance from nose of model. meter Angle-of -attack reference Fuselage length. meter . Wing (based on A = 16O) Area. S. meter2 . Span. b. meter Mean aerodynamic chord. E. meter Aspect ratio . . Taper ratio Dihedral angle. deg . Airfoil section I Vertical
28、tail Area. meter2 . Span. meter Tip chord. meter . Root chord. meter . Taper ratio Aspect ratio Leading-edge sweep angle. deg Trailing-edge sweep angle. deg Airfoil section . Airfoil thickness/Chord ratio . 1 Horizontal tail Area (total). meter2 . . Span. meter Tip chord. meter Root chord. meter Tap
29、er ratio . . Aspect ratio Leading-edge sweep angle. deg . Trailing-edge sweep angle. deg . Dihedral angle. deg . Airfoil section Airfoil thickness/Chord ratio: Root Tip . Conflgurztion A 1 Configuration 9 Configurations A and B 0.036 0.260 0.038 0.208 0.186 1.88 57.5 15.1 0 Biconvex 0.564 0.577 Body
30、 reference line 0.940 Configuration A 0.1009 0.8729 0. 1253 7.56 0.325 0 NACA 64A2XX 0.489 0.502 Body reference line 0.86 5 Configuration B 0.1055 0.9699 0.1219 8.91 0.251 0 NACA 64A2XX Configurations A and B 0.0235 0.151 0.053 0.208 0.255 2.32 55.0 22.0 Biconvex 0.04 Provided by IHSNot for ResaleNo
31、 reproduction or networking permitted without license from IHS-,-,-TABLE n.- DYNAMIC STABILITY CWARACTERISTICS a PITCH OF BASIC CONFIGURATION A Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE 11. - DYNAMIC STABILITY CHARACTEHSTICS IN PITCH OF B
32、ASIC CONFIGURATION A - Concluded Mach number, 0.80 0.80 0.80 0.80 0.80 0.80 0.80 0.80 0.80 0.80 0.80 1.00 1.00 1.00 1.00 1.00 1.00 1.00 1.00 1.00 1.00 1.00 1.20 1.20 1.20 1.20 1.20 1.20 1.20 1.20 1.20 1.20 1.20 Mean angle of atlack, a.deg 0. -2.00 -1.00 -001 1.00 1.99 4.00 6.00 8.00 10.00 12.00 0. -
33、2.00 -1.00 -0.01 1.00 2.00 3.99 5.99 8.00 10.00 12.00 0. -2.00 -1.00 0. 1.00 2.00 4.00 6.00 8.00 10.00 12.00 Mach number, 1.70 1.70 1.70 1.70 1.70 1.70 1.70 1.7C 1.70 1.70 2.16 2.16 2.16 2.16 2.16 2.16 2.16 2.16 2.16 2.16 2.16 2.16 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 2.50 Damping
34、parameter, Cmq+ Cmc.g.al 40C -0.65 -0.72 -0.60 -0.66 -0.76 -0.93 -1.74 -1.96 -2.83 -2.20 -2.33 -0.90 -1.17 -0.91 -0.91 -1.01 -1.32 -2.35 -2.90 -4.14 -3.97 -3.51 -1.90 -2 .OO -1.89 -1.89 -2.04 -2.30 -2.96 -3.64 -4.02 -3.78 -3.85 - Reduced- frequency k .3104 .016 .0103 .0104 .0106 .0110 -0125 .GI29 .0
35、143 .0133 .0135 .GO92 .0097 0092 .0092 -0094 .0099 -0116 .0124 .0140 -0138 .0132 .0096 .0098 .0096 ,0096 .0098 .dl02 .0111 .0119 .0123 .0120 .Dl21 Mean angle of attack, a. deg 0.48 -0.51 1.48 2.47 4.47 6.47 8-46 16.46 6.47 3.48 1.42 0.43 -i.56 -2.56 -4.58 2.41 3.44 5.42 7.43 9.45 11-45 1.45 1.07 0.1
36、0 -0.91 -2.94 -4.93 2.09 3.10 5.06 5.79 9.06 11.11 1.C6 Domping parameter, Cmq+ per radian Oscillatory- C,-C, d per Reduced frequency parameter, k .CC5h .OC55 .CC57 .CC59 .CC)63 . n65 . nC65 . CC64 .CC65 .re56 .CC49 .CC47 SC46 AC47 .049 .015C .C:50 .or51 .PC51 .a050 .r)C49 .en49 .CC44 .CG43 .OC43 .C
37、C44 .0C44 .Or45 .C45 .0345 .0045 .C045 .CC44 .PO44 A=72.5* - -3.5 -31.3 -31.2 -27.7 -32.1 -29.7 -30.6 -24.1 -34.6 -27.8 -2d.o -22.8 -24.8 -2,.6 -33.7 -24.1 -2).1 -23.1 -32.0 -34.2 -38.5 -21.4 -27.1 -23.6 -22.0 -22.4 -45.0 -28.1 -12.7 -25.4 -23.2 -41.8 -20.7 -29.2 ; c.g.0 1 0.40E -1.98 -1.87 -2.17 -2
38、.42 -2.98 -3.20 -3.13 -3.09 -3.16 -1.98 -2.10 -1.83 -1.68 -1.77 -1.97 -2.16 -2.14 -2.28 -2.28 -2.24 -2.C8 -2.11 -1.76 -1.b6 -1.69 -1.79 -1.73 -1.89 -1.95 -1.99 -1.98 -2.P2 -1.81 -1.78 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE BE, - DPNAWC
39、 STABILITY CHARACTERISTICS IN PITCH OF BASIC CBNBGURATION A WITH it - -26“ TABLE IV. - DYNAMIC STABILITY CHARACTERISTICS IN PITCH OF BASIC CONFIGURATION A WITH OSCILLATION AXlS AT 0.30E Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE V. - DYNAM
40、IC STABILITY CHARACTERISTICS IN PITCH OF BASIC CONFIGUFtATTON A WITH GLOVE REMOVED Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE VI. - DYNAMIC STABILITY CHARACTERISTICS IN PITCH OF BASIC CONFIGURATION A WITH WING AND GLOVE REMOVED AND OSCILLA
41、TION AXIS AT 0.30E Mach number, 0.40 0.40 0.40 0.40 0.40 C.4C 0.40 0.40 0.40 0.40 6.40 0.40 C.60 0.60 C.60 0.60 C.60 0.60 0.60 0.60 0.60 0.60 0.60 0.60 0.63 C.80 0.80 0.80 0.80 0.80 0.8C 0.80 0.80 0.80 0.80 C.80 0.80 angle of parameter, attack. Cmq+ Crnh a, deg per radian per Horizonfal toil on -0.0
42、1 -22.7 -2.01 -23.7 -1.02 -24.4 1.01 -23.8 2.00 -24.8 4.00 -26.9 6.00 -27.4 8.00 -27.3 10.00 -21.8 12.00 -20.1 14.CO -22.0 16.00 -28.6 0. -1.99 -23.9 -0.99 -22.9 -0.01 -24.5 1.01 -23.0 1.58 -24.4 4.01 -27.7 6.01 -28.0 8.01 -25.2 9.99 -28.4 11.95 -30.1 14.02 -30.7 15.99 -30.8 -0.01 -22.2 -2.00 -24.4
43、-0.98 -23.0 6.98 -24.3 2.01 -25.9 4.01 -24.0 6.01 -29.0 8.02 -31.3 10.00 -31.7 11.99 -34.5 13.98 -34.7 15.95 -30.6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE VII. - DUNAMIC STABILITY CHARPICTERISTICS IN PITCH OF BASIC CONFIGUIRATION A WITH
44、 WING GLOVE REMOVED AND OSCILLATION AXIS AT 0.40E Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE VIII. - DYNAMIC STABILITY CHARACTERISTICS IN PIT
45、CH OF BASIC CONFIGURCBTION A WITH HORIZONTAL TAIL REMOVED - Concluded Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE K, - DYNAmC STABILITY CRARACr%ERES%16;“S IN PlrI“CH OF BASIC COWEIGVIRATJON A WITH ENGINE IN LETS PLUGGED TABLE X. - DYNANHC S
46、TABILITY CHARACTERISTICS IN PITCH OF CONFIGURATION B M Mean Damping OcillatarY- Reduce A=72.5 ;c.g.at 0.40 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABIAE XI, - DmAMICI STABILITY CHARACTENSTICS IN YAW OF BASIC CONPICUMTION A Provided by IHSNot
47、 for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE XI, - DmAMXC STABTLlTY CHARACTERISTICS IN lyAT$4 OF BASIC CONPIGUMTION A - Coneluded number, i Yh Angle of attack, (1 I ( deg 1 per radian 1 7er radian 1 I -per radian- I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABIAE XI,- DmiWC STABILITY CH&ACTER%STICS IN YAW UP BASIC CONFIGISRATION A WITH it = -20 - Damping Osclllat0r- Reduced- Ef fecfive- Stability frequency dihedral parameter, parame
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