NASA NACA-RM-A8D02-1949 Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees - investigation of a large-scale model at low speed《采用63后掠翼机翼和机身组合的空.pdf

《NASA NACA-RM-A8D02-1949 Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees - investigation of a large-scale model at low speed《采用63后掠翼机翼和机身组合的空.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-RM-A8D02-1949 Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees - investigation of a large-scale model at low speed《采用63后掠翼机翼和机身组合的空.pdf（22页珍藏版）》请在麦多课文档分享上搜索。

1、RESEARCH MEMORANDUM . . . AERODYNAMIC STUDY OF A WING-FUSELAGE COMBINATION EMPLOYING A WING SWEPT BACK 63O. - INVESTIGATION m r OF A URGE-SCALE MODEL AT LOW SPEED By Gerald M. McCormack and Walter C. hori ty NATIONAL ADVISORY COMMITTEE % I I L FOR AERONAUTICS WASHINGTON Jmuary 21,1949 Provided by IH

2、SNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-EMPLOYITG A WIERT SWEPT BACK 63O.- INVESTIGATIOPI OFAUX it did, however, decrease the dihedral effect and contributed a destabilizing increment of about -0.0012 to the directional stabilfty of the wing. The rehticmEh

3、ip8 between the force and mament charactsristice and flow conditions existing over the wing are dLECUf3ed In the report. The theory developed in reference 1 indicakss that aircraft employing wFnge of high Bweepback and high aspect ratio should be capable of efficient flight (L/D 10) at moderate supe

4、rsonic Mach numbers. To provide information necessary for the desi- of such 89 airplane, a possfble configuration for a traneport-typ amlane suitable for f Ught at epee was tested alone and in catbination with the fueelebge. Sixrccanponent fmce and m-nt data were obtained tbr- an me- ofdttack range

5、at ecch of eeveral angles of aideslip. The data were obtained at a dyrmxtc preseure of 25 pounds per square foot (a Reynolde number of 8 x 10 based upon the mean aerodynamic chord of 8.64 ft) , The win it did, however, decreaae the dihedral effeot about 3 and contributed a destabilizing increment of

6、 about -0.0012 to the direotimal stability of the wing. Ams8 Aeronautical Laboratory, Rational Advisory Cannnittee for Aeroneutics, Moffett Field, Calif. 1. Jone8, Robert T. : Estimated Lift-Drag Ratio8 at Buperecmio Speed. IWCA TN No. 1350, 1947. 2. DeYorzng, John: Theoretioal Aaditiond Bpn Loading

7、 Character- ietica of Wings with Arbit- Ehmep, Aspect htio, and Taper mtio. WA !QV Bo. 1491, 1947. 3. Jones, Robert T. : Eff eots of Sweepback on Boundary Lapr and Separation. WA 93I No. 1402, 1947. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-flp

8、we f .- Standard NACA si convention. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-10 I mACA RM No. Am 63. #8.3sqff 0 l 1 Fiwre Z.-Gemetr/c churocteristics of 63“ swept-bock wing plus fuseloge. Provided by IHSNot for ResaleNo reproduction or networ

9、king permitted without license from IHS-,-,-t Figure 3.- Photogram of 63O ewephback wing mounted In AIWS 40- by &foot and tunnel. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I Provided by IHSNot for ResaleNo reproduction or networking permitted w

10、ithout license from IHS-,-,-WCA FM No. A8DO2 13 Figure 4.- Photograph of 63O ewepbback wiqpfueelage combfnation mounted in Ames h.& by &foot wind tunnel. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or

11、networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-fW 5.- ctn7&d?d, . . . . . . . . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNo

12、t for ResaleNo reproduction or networking permitted without license from IHS-,-,-.“ . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-mACA RM No, 0 002 e, %002 P Provided by IHSNot for ResaleNo reproduction or networking permitted without license

13、 from IHS-,-,-figure 8.- Comporison bet ween experimenfal and fheorefrcal longitudinal chzrrocterisfics of 63 swepf-buck wing. 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-,-,-