NASA NACA-RM-L7E13-1947 Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degrees Sweptback Wing at Reynolds Numbers to 8 000 000《当雷诺数为8 000 000时 机身对42后掠翼空气动力特性的影响》.pdf

《NASA NACA-RM-L7E13-1947 Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degrees Sweptback Wing at Reynolds Numbers to 8 000 000《当雷诺数为8 000 000时 机身对42后掠翼空气动力特性的影响》.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-RM-L7E13-1947 Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degrees Sweptback Wing at Reynolds Numbers to 8 000 000《当雷诺数为8 000 000时 机身对42后掠翼空气动力特性的影响》.pdf（34页珍藏版）》请在麦多课文档分享上搜索。

1、RESEARCH MEMORANDUM c I EFFECTS OF A FUSELAGE ON THE AERODYNAMIC CHARACTERISTICS OF A 42 SWEPTBACK WING AT REYNOLDS NUMBERS TO 8,000,000 Rein0 J. Salmi, D. William Comer, and Robert R. Graham Langley Memorial Aeronautical Laboratory Provided by IHSNot for ResaleNo reproduction or networking permitte

2、d without license from IHS-,-,-The effects of a fuselage on the low-speed aeroclynamic charm- teristics of a sweptback wing were investigated in the Langley 19-foot pressure tunnel. Test8 were made in pitch at Reynolde of 1,72O,OOO and 5,300 COO-. The wing had an aspect ratio of 4, taper ratio of 0.

3、625, c2 sweepback at the leading edge, and representattie fuselage of cfrcular cms8 section W090,000 for testa in pitch and of 1,720,000 +nd 5,300,000 for tests in yaw. Theso data am presented together xith - aorrespondlng wing,d.one data from mference 1. CI;, lift coefficient (Liff/qS) Provided by

4、IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3 MO free-stream Mach number (Vfa) U angle of attack measured in plane of synrmetry, degrees rlr angle of yaw, positie when rirter-chord line of a etraight wing penel which has been rotated bo about the quarter- ch

5、ord point of the root chord, The aspect ratio ie 4, taper ratio, 0.625, and the tips am rounded in plan form and crom section b9g-W at 97.5 percent of the semispan Them is no geometric dihodral or twist. !Phe fuselage is circular in croea section and tapers to a polnt at each end. The maximum diamet

6、er, which fs oonstant at the wlng interaection, is equal. to 40 percent of the wing chord (measured at the plane of synrmetry), and the fineness ratio is 10.3 The center portion of the fumlage has removable blocks to permit tho mounting of the wing at hie-wing, low-wing, and midwing positions with 2

7、O incidence between the wing chord plane and the fuselage center line. No fillets were used at the wing-fuselage juncture for any wing PO sition The eplit flaps were fabricated of aheet steel and extended from 12.3 to 50 percent of the wlng seznlspan. The center gap wm maintained to facilitate flap

8、defloction. The flap chord is 18.4 per- cent of the local wing chord. .The flap deflection measured from the lower aurface of the wing and in a plane normal to the hinge line is 6oo. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-me mod61 wae testei

9、on the top of the yaw supprt waa shieiilea W the same fairing used for *e wing alone tests (reported in referenoe 1). The .pitch tests were made at Reynolds nttmber values of 3,04C),OOO (Mo = 0,969) and 8,09o,c00 (G = 0.19) . The tests were mede with and without split flaps. stallcharaoteristics wer

10、e studied by mean8 of wool tufts attached to the uppereurface of the wing beginning at percent of the wing chord, The lateral-stability parameters were obtained from tests through an angle-of-attack rqe of yaw ea of 00 and eo, at Beynolds.number values of 1,720,OOO (M, = 0.10) and 5,300,000 ( zero l

11、ift for tho midm combination. With flaps on, the high-wiw and low-wing positions had values of taper ratio = 0.625; area = 4643 sq in.; F = 34.7 in. No dihedral or twist. (All dimensions in inches.) Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. .

12、 . . . . . . . - . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . -. . . . . . . . . . . . . . . E 0 (a) High-wing fuselage combination on pitch suppork. Figure 3.- The 42 sweptback wing and fuselage mounted for testing in the Langley lQ-foot Y pressure tunnel. F E Provi

13、ded by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No. L7E13 Fig. 3b (b) Pitch support details. Figure 3.- Continued. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . (c) Low-wing fuselage combinat

14、ion on yaw support, Figure 3.- Concluded. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. , . . . . - . . . . . . . . . . . . . . , . . . . . . . . . . . . . . . . . . . . . . . . , . . . . . . . . . . . . . . . Provided by IHSNot for ResaleNo repr

15、oduction or networking permitted without license from IHS-,-,-. . . . . . . . . . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . . . . . . . . . . . . . . . - I Provided by IHSNot for ResaleNo reproduction or networking permitted wit

16、hout license from IHS-,-,-“. . . 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-,-,- . Provided by IHSNot for ResaleNo reproduction or networking per

17、mitted without license from IHS-,-,-. . . . . “. 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-,-,-NACA RM No. L7E13 Fig. 8 . Figure 8.- Yarlation o

18、f dddC with Ct for a 420 sweptback wing alone and mounted at three varticafi positions on a fuselage. R = 8,090,000. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 9a NACA RM No. L7E13 . Provided by IHSNot for ResaleNo reproduction or networkin

19、g permitted without license from IHS-,-,-NACA RM No. L7E13 Fig. 9b Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 10a NACA RM No. L7E13 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No

20、. L7E13 Fig. 10b . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 11 NACA RM No. L7E13 (a) R = 5,300,000. (b) R = 1,720,000. Figure 11.- Effects of a fuselage .on C of a Go sweptback wing for three vertical poaitions of the wing. v . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No. L7E13 Fig. 12s Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-