NASA NACA-RM-L9E02-1949 The effect of span and deflection of split flaps and leading-edge roughness on the longitudinal stability and gliding characteristics of a 42 degrees sweptb襟.pdf

1、“ RESEARCH MEMORANDUM THE EFFECT OF SPAN AND DEFLECTION OF SPLIT FLAPS AND LEADING-EDGE ROUGEtNESS ON THE LONGITUDINAL STABILITY AND GLIDING CEWRACTERBTICS OF A SWEPTBACK WING EQUIPPED WITH LEADING-EDGE FLAPS BY . d. =T George L. Pratt and Thomas V. Bollech ci z Langley Aeronautical Laboratory C? La

2、ngley Air Force Base, Va. t“ I 42 NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS WASHINGTON June 21,1949 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-0 NACA RM LgE02 NATIONAL AwISClRY C0“TX FClR AERONADIICS By George L- Pratt and Thamas V. Bollech Th

3、e effect of half-span and full-span Bplit flaps through a deflection range of 00 to 6oo on the low-speed, longitudinal charac- teristics of a sweptback wing equipped with round-nose, extensible, leading-edge flaps .wa investigated at a Reynolde number of 6.8 X 106. . Additional tests were mad at a l

4、ower Reynolds rider to dethne * the effect of leading-edge roughness on the lqitudlnal stability of the sweptback wing equipped with 0.725-sdspa and 0.575-samispan lea-edge flaps. The wing had 42.05O sweep at the leading edge, 821 aspect ratio of 4.01, a taper ratio of 0. 5, and RACA 641-112 -/3.4“

5、. /.38 C-/8.5“ p1.52 A cz- /9.6O (a) Split flaps off. (b) Half-span eplit flaps. . (c) Full-span split flaps. Figure 7. - Stalling characteristics of the 42O aweptback wing 4 with 0.579 lead3ng-edge flaps snd. trailing-edge split flaps. 6f = 60; R = 6.8 x d. 2 . “ Provided by IHSNot for ResaleNo rep

6、roduction or networking permitted without license from IHS-,-,-NACA FM LW2 . Figure 8. - Glide characteristics of a 42 smptback wing with 0.579 2 leading-edge flaps at various split-flap deflections. Wing loading, 40 porn R = 6.8 x 10 6 . Provided by IHSNot for ResaleNo reproduction or networking pe

7、rmitted without license from IHS-,-,-20 WACA RM L9E02 40 /o 40 30 v, fPS 88 IO0 /20 Half-span split flap, (3 1.2 v, 200 (b) Pull-span split flap. Figure 9.- Effect of eplit flaps on the gliding characteristics of the 42O sweptback wing. Provided by IHSNot for ResaleNo reproduction or networking perm

8、itted without license from IHS-,-,-/.6 i. 4 .4 0 . , . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-L4 I. 2 i.0 .8 .6 .2 0 -. 2 -. 4 (a) Spllt flaps off; Bp = 60; R = 4.7 x 10 .

9、 Pigure ll.- Aerodynamia charactariatics of a 42 mptback wing with 0 -57% lea-eage flags with and without Isading-eage romess. 6 b 1 1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I. 6 I. 4 1.2 1.0 0 . - . I (b) Half-span split flaps mj 9 = 63; R

10、= 3.0 x 10 . 6 .4 0 4 8 I2 I6 20 24 28 O 04 708 :I2 716 a: deg . OB .I2 . I6 .20 .24 .28 .32 .36 Gm 6 w n) 1 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-24 NACA RM 902 cL= /. 40 A Cf /. 46 E= 20.5“ A c,= /.44 h G= /9.s . Provided by IHSNot for

11、ResaleNo reproduction or networking permitted without license from IHS-,-,-. CL = 0.97 LC= /6.0“ A LedIng edge smooth Leding edge rough (a) SpUt flqs off; R = 4.7 x lo6. Fiwe l3.- Effect of roughness on the stalling characteristics af the 42 sveptback wing with 0 .!7= /7.4 O A c,= l.31 * a= /9.4O L 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-,-,-