NASA NACA-RM-L50H29-1950 Positioning investigation of single slotted flaps on a 47 7 degrees sweptback wing at Reynolds numbers of 4 0 x 10(exp 6) and 6 0 x 10(exp 6)《在雷诺数为4 0x10(指.pdf

《NASA NACA-RM-L50H29-1950 Positioning investigation of single slotted flaps on a 47 7 degrees sweptback wing at Reynolds numbers of 4 0 x 10(exp 6) and 6 0 x 10(exp 6)《在雷诺数为4 0x10(指.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-RM-L50H29-1950 Positioning investigation of single slotted flaps on a 47 7 degrees sweptback wing at Reynolds numbers of 4 0 x 10(exp 6) and 6 0 x 10(exp 6)《在雷诺数为4 0x10(指.pdf（38页珍藏版）》请在麦多课文档分享上搜索。

1、RESEARCH MEMORANDUM NATIONAL ADVISORY COMMITTEE WASHINGTON October 9, I950 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-WCA RM LwH29 -. . . - . - . “ NATIONAL ADVISORY COMMrmTEE FOR AERONAUTICS POSEIORING INVESTIGATION OF SINGLE SLOTTED FLllps ON

2、A 47.7 SGlEpTBACK WING AT REYNOLDS N“ OF 4.0 X 10 AND 6.0 X io 6 6 By Stanley H. Spooner and Ernst F. Mollenberg SUMMARY A low-speed wind-tunnel investigation has been conducted at Reynolds numbers of 4.0 x 10 and 6.0 x lo6 to determine the relation- ship between the fhp effectiveness and the horizo

3、ntal and vertical position of a partial-span single slotted flap on a 47.7O sweptback- wing - fuselage combination. The wing had an aspect ratio of 5.1, a taper ratio of 0.383, and NACA 64-210 airfoil sections. . 6 The value of the maximum lift coefficient is relatively unaffected by the wing-flap p

4、osition or the flap deflection within the range inves- tigated. The increment of lift coefficient in the linear-lift range, however, varies with flap position and increases with increasing flap deflection. Although the opthum flap position (position of largest lift increment) on 8 47.70 sweptback wi

5、ng is not predicted exactly by two-dimensional tests, the reduction of the increment of wing Uft coef- ficient as a result of the use of the optbum flap positions determined from two-dimens-ional tests amounts to only 0.02 to 0.03. INTRODUCTION The sensitivlty of the maxFrmrm lift coefficient to mal

6、l changes in the position of slotted flaps with relation to the airfoil is shown in reference 1. In the past, two-dimensional tests have been used as. the basis for determining the optinrum position of these flaps on unswept wings. ,. With the advent of swept wings there has been some question as to

7、 e the validity of basing swept-wing flap positions on two-dimensional tests. Furthermore, considerations of the stalling characteristics of. some sweptback wings indicate that the wing maxinrum lift coefficients - 3lEYTEm -2 Provided by IHSNot for ResaleNo reproduction or networking permitted witho

8、ut license from IHS-,-,-2 NACA RM L5OH29 may be relatively insensitive to changes in the slotted-flap position so that the optimum flap position must tlieh be establi-shed on a basis other than maximum lift. An Investigation was undertaken, therefore, to establish the rela- tionship of the optimm fl

9、ap positions on a sweptback wing to those determined from two-dimensibd tests and to e.iaiu sf = 30; R = 4.0 x 10 6 . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . . . . . . . . . . . . . . (b) CL against CD. Figure 6.- Continued. I I

10、 . . . . . . . . . . . . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I I . L m (c) cL against k. Figure 6.- Concluded. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6 . . . . . . . . 14 6 .4

11、 2 0 -4 0 4 8 P si372428 0 0 0 0 0 4 8 L?/6202428 0 0 A h d; dim (a) CL against a. I 1 . . . . . . . “. . . . N c z ul r 8 o I . . . . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . I t IP L I UI N Provided by IHSNot for ResaleNo reproductio

12、n or networking permitted without license from IHS-,-,-. . . . . . . - . (c) CL against af = 4oo; R = 4.0 x 10 5 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . . . . . . . . . (b) CL against Figure 8.- Continued. 0 1 I . . . . . . . . . . . . . . . . . . . . . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I I P (c) CL against c,. Figure 8.- Concluded. . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-