NASA NACA-TN-4146-1958 Contribution of the wing panels to the forces and moments of supersonic wing-body combinations at combined angles《在联合角度下 翼板对超音速机翼机身组合力量和力矩的促进》.pdf

1、0$=coLdNATIONALADVISORYCOMMITTEEFOR AERONAUTICSTECHNICAL NOTE 4146CONTRIBUTION OF THE WING PANELS TO THE FORCESAND MOMENTS OF SUPERSONIC WINGBODYCOMBINATIONS AT COMBINED ANGLESBy J. Richard SpahrAmes Aeronautical LaboratoryMoffett Field, Calif.WashingtonJanuary 1958Provided by IHSNot for ResaleNo re

2、production or networking permitted without license from IHS-,-,-TECH LIBRARY KAFB, NMIilllllflulllllllNATIONAL ADVEORY COMMITTEE FOR AERONAUTICS0Clb7UiiTECHNICAL NOTE 4M-6CONTRIBUTION OF TEEAND MOMENTS OFCOMBINATIONSWING PAKELS TO TKE lK)RCESSUPERSONIC WING-BODYAT COMBINED ANGLESBy J. Richard SpahrS

3、UMMARYA wind-tunnel investigation was conducted at a Mach number of 1.96and at Reynolds numbers (based on the mean aerodynamic chord of theexposed wing) of 0.36 snd 1.03 miUion to determine the normal forcespitching moments, and rolling moments contributed by ea *g P=el ofa cruciform-wingand body co

4、mbination over a wide range of combinedangles of pitch and roll. The wings were trismgular of aspect ratio 2,and the body was an ogive-cyldnder combination. The effects of forebodyernate forebodes (porti:d;1.(Bl)(B2).(B3).The factor C% represents the nomal-force-cuxve slope of a two-dimensional wing

5、 having a sweepback of A -. The spamntse distributionof upwash induced by sn incompressible inviscid two-dimensionalvortex isgiven byw r Y-Y-=v 2XV ZV2+ (y-yv)2 (B4)The spanwise variation of the chord of a general plan form hatig straightedges can be expressed byc-= A-B:a (B5) a71Provided by IHSNot

6、for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN 4U6.27coAa=snd the lontudinal. center-of-pressurelocation of each strip of constantloading by(B6)wherec =D=co- tan A2atan A- (1-x)If equations (Bk), (B), and (B6) are substituted into (Bl), (B2), -d (B3),.and the

7、integrations are performed, %.H+(S-SN=+BC):-Aclfd!+Bw=D3:f4(B7)-*.(B8) -Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-28(A -B%f.-(A+2B 5E-JY YV2+B 2whereZV2+ (Sm- YV2f= = inZV2 + (a-yv)Z-Yv -la-yvf .ts31-lfi - z z(9).Provided by IHSNot for ResaleNo

8、 reproduction or networking permitted without license from IHS-,-,-NACA TN 4146 29REFERENCES1. Fttts, WIUi_sm C., Nielsen, Jack N., and Kaattari, George E.: Liftand Center of Pressure of Wing-Body-Tail Combinations at Subsonic,Transonic, and Supersonic Speeds. NACA Rep. 1307, 1957.2. Spreiter, John

9、R.: The Aerodynamic Forces on Slender Plane- andCruciform-Wing smd Body Combations. NACA Rep. 962, 1950.3. Spreiter, John R., and Sacks, Altin H.: A Theoretical Study of theAerodynamics of Slender Cruciform-WingArrangements snd Their Wakes.NACA Rep. Q96, 1957. (SupersedesNACA TN 3528)4. Jorgensen, L

10、elsnd H., and Perkins, Ednrd W.: mvestietion of time ._Wake Vortex Characteristics of an clined Ogive-CylinderBody atMach Number 1.98. NACA RM A5X31, 1955. Wrikawa, George: Supersonic Wing-Body Lift. Jour. Aero. Sci.,vol. 18, no. 4, Apr. 1951, pp. =7-228.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-