NASA NACA-RM-L53A29-1953 Low-speed lateral control characteristics of an unswept wing with hexagonal airfoil sections and aspect ratio 4 0 at a Reynolds number of 6 2 x 10(exp 6)《当.pdf

《NASA NACA-RM-L53A29-1953 Low-speed lateral control characteristics of an unswept wing with hexagonal airfoil sections and aspect ratio 4 0 at a Reynolds number of 6 2 x 10(exp 6)《当.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-RM-L53A29-1953 Low-speed lateral control characteristics of an unswept wing with hexagonal airfoil sections and aspect ratio 4 0 at a Reynolds number of 6 2 x 10(exp 6)《当.pdf（26页珍藏版）》请在麦多课文档分享上搜索。

1、SECURITY INFORMATION 1.: f L“ RESEARCH MEMORANDUM LOW-SPEED LATERAL CONTROL CHARACTERISTICS OF AN UNSWEPT WING WITH HEXAGONAL AIRFOIL SECTIONS AND ASPECT RATIO 4.0 AT A REPMOLDS NUMBER OF 6.2 x 10 By William M. Hadaway Langley Aeronautical Laboratory Provided by IHSNot for ResaleNo reproduction or n

2、etworking permitted without license from IHS-,-,-1w NACA RM L53A29 NATIONAL ADVISORY CObMlTT3Z FOR AXRONAUTICS -. . r RFSEARCH “3F#“ L LOW-SPEED UTEFUiG CONTFtOL CHARACTERISTICS OF AN UNSWEPT By Willim M. Hadaway A lateral-control investigation has been made in the Langley 19-foot pressure tunnel of

3、 an unswept WLng having 6-percent-thick hexagonal air- foil sections, aspect ratio 4.0, and taper ratio 0.625. The wing was mounted on a circular fuselage with a fineness ratio of 10 to 1. Char- acteristics of both a 0.40 semispan outboard aileron and a 0.79 semispan of 0.79 semispan leading-edge fl

4、aps and 0.39 semispan trailing-edge flaps were also determined. The data include aileron normal-force, as force measurements by the standard six-comgonent balance system. A theoretical aileron effectiveness value Cz8 of 0.00132 compared with an experimental value of 0.00250 for the plain wing equipp

5、ed with the 0.40 semispan aileron. Comparisons of the rates of change of the hinge moment with aileron deflection and angle of attack as well a8 of the unswept wing with those of an unswept wing of aspect ratio 2.5 having the same wing area, taper ratio, and airfoil section are also presented herein

6、. c aileron were investigated at a Reynolds neer of 6.2 X lo6. The effects Y hinge-moment, and aileron balance-chaniber-preseure measurements as well cz8 INTRODUCTION As part of the study of the low-speed characterfstics of wings suit- able for supersonic spee however, there fs a scarcity of data pe

7、rtaining to aileron hinge moments. aileron normal r conducted at the Anmes Laboratory by Ben E. Johnson, Jr . , and Red A. I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 NACA RM L53429 Sorces, and aileron balance-chamber pressures. This paper pr

8、esents force measurements as well as aileron hinge moments, normal forces, and balance-chamber pressures. The tests included measurements of both 8 0.79 semispan and an outboard 0.40 semispan aileron. The eflects of leading-edge droop and part-span trailing-edge flaps on the outboard aileron effecti

9、veness were also investigated. All tests were made with a cylindrical fuselage attached to the wing. No analpis is presented herein. SYMBOLS AND comcms The data are referred to wind axes wfth the origin at 25 percent of the mean aerodynamic chord projected to the plane of symmetry. Symbols and coeff

10、icients are defFned aa follows: S wing therefore, for these anglee the dynamic pressure w88 Lovered to 60 pounds er square foot, which corre- This small Reynolds rimer change had no appa;rent effect on the trends and magnitudes of the data. presented. c sponded to a Reynolds mer of 5.36 X 10 and a M

11、ach mriber of 0.13. 8 The lift snd pitching-moment coefficients (fig. 3) have been corrected for air-streammiealinement and for support tare and inter- ference effects. The aynamic pressure has been corrected for blocwe in the test section. Jet-bounda3y correctiom, based on the method of reference 2

12、, have been applied to. the angle of attack but were found to be negligible for the pitching-moment coefficient, yaxing-moment coefficient, and rolling-moment coefficient and were not applied. Variations of rollhg-moment and yming-moment coefficients at 8a = 0 through the angle-of-attack range were

13、obtained for both the plain wing and the wing with leading- and trailing-edge flaps deflect- Edge Flaps on the Lar-Sped Characteristics of the Wing. NACA RM A S, 28 square feet; A, 0.625. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-C t I I . . Pr

14、ovided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . .- Figure 3. - c-101 of lFft and pitching-mcsnent coefficient of the subject aspect ratio 4.0 wing with that of a wing of aspect ratio 2.5 having the sam wing area, taper ratio, and ahfoil secti

15、on. 8f = 50; B, = 300. I . . . . . . “. . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM L53A.29 .O/ - .O/ . o/ -.O/ .O/ -. o/ . 01 -.O/ 0 Original run 6 Check run Leading and trailin - edge flaps defleote8 Leading and trailing-edge flapa de

16、flected -4 0 4 8 /2 16 PO 24 Q?, dQ Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-12 c NACA RM L53A29 .04 473 .02 .O/ 0 4 70. -03 -.04 (a) Variation of C, and CZ with a. Figure 5 .- Variation of hY CzY Ch, pRy and CN with a; 0.40b/2 outboard ailero

17、n. Plain wing. “ Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.28 ./6 .OB .04 0 -04 = O.79b/Z leading-edge flaps, 0.39b/2 trailing-edge flaps, 0.40b/2 outboard aileron. 6f = 50; 8, = 30. - Provided by IHSNot for ResaleNo reproduction or networking

18、 permitted without license from IHS-,-,-NACA RM L53A29 - 24 20 ./6 .OB 94 0 :04 -32 -36 -.40 - (b) Variation of Ck with a. Figure 7. - Continued. 1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-20 v NACA RM L53A29 LO .8 .6 -4 clv, .P 0 -.a -.4 -.6

19、-8 -8 -4 04 8 12 16 20 24 2% q del7 Figure 7. - Concluded. - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM L53A.29 w 21 .003 .002 .oo/ 0 C 2s Figure 8.- The effects of aileron span and leading- and trailing-edge flaps on the aileron hinge m

20、oment and effectiveness pEaramters Cz6, SY ch pk= Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-22 IWCA RM L53A29 Asgeot ratio 4.0 “ Asgeot ratio 2.5 .UO3 ,002 DO / 0 . Figure. 9.- Comparison of afleron effectiveness of the subject 28 aspect ratio

21、4 .O wing with that of a wing of aspect ratio 2.5 having the same area, taper ratio, and airfoil section. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM L5-29 0 . Plain rring (0.40 b/2 outboard oileron) 0 - Figure 10.- Comparison of ch, of t

22、he subject aspect ratio 4.0 wing with that of a wing of aspect ratio 2.5 having the same area, taper ratio, and airfoil section. Im Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-24 6 NACA RM L53A29 0 Aspect ratio 4.0 : 004 ,008 “ Aspect ratio 2.5 C

23、 8 I 5012 U : 016 7008 Plain winp (0.79 b/2 aileron) 0.79 b/2 leading-edge flap8 and 0.39 b/2 trailing-edge flaps (8n = fO*, = 50 ). 0.40 b/2 outboard aileron. Figure U.- Camparison of C, of the subject aapect ratio 4.0 wing 6 with that of a wing of aspect ratio 2.5 having the same area, taper ratio, and airfoil section. - Nm-hngley - 8-20-63 - 925 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-