NASA NACA-RM-A54D19-1954 Pressure distributions on triangular and rectangular wings to high angles of attack - Mach numbers 1 45 and 1 97《在马赫数为1 45和1 97时 三角形和矩形机翼的高攻角压力分布》.pdf

《NASA NACA-RM-A54D19-1954 Pressure distributions on triangular and rectangular wings to high angles of attack - Mach numbers 1 45 and 1 97《在马赫数为1 45和1 97时 三角形和矩形机翼的高攻角压力分布》.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-RM-A54D19-1954 Pressure distributions on triangular and rectangular wings to high angles of attack - Mach numbers 1 45 and 1 97《在马赫数为1 45和1 97时 三角形和矩形机翼的高攻角压力分布》.pdf（28页珍藏版）》请在麦多课文档分享上搜索。

1、262copyRM A54D19. -.-.-=LIN“-_ .,- .,. -RESEARCH MEMORANDUMPRESSURE DISTIUBUTIONJS ON TRIANGULAR AND RECTANGULARWINGS TO HIGH ANGLES OF ATTACK -MACH NUMBERS 1.45 AND 1.97By George E. KaattariAmes Aeronautical Laboratory )Moffett Field, Calif.Fey *. b.w KJ.Jw 10.4?.3 (;$.k?6.W.W 1I.?#?l.*.h03.41J.%2%

2、?.k?3.4W 10.W9.WEj.!45 1“;$.4*.439.b 1).0% 1.OL?s.C53.: y-=h”d.155 .145 d.152 .124! ” -17 Rear view.,=1;3!iProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-180 .2 4 .6 .8 LONACA RMA54D191614121086420 .2 4 .6 .8 LOSpanwise location, y/s(a) Span loading

3、.z 1.6-.%$1.2 .88T Linear Theory = .4 Experimental dataso 5 10 15 20 25 30 35 40 45 50 :.Angle of attack,a,deg. .5(b) Noml-force curves.Figure 2.- Aerodynamic characteristics of wing 1.4,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.NACARMA54D19.7

4、0.68.66.64centroid ofwing area/ ,!5.70 “.68 .66 c%.64 .32(c) Center-of-pressure position; M = 1.45.centroid of.34 .36 .38Spanwise location, /s!40(d) Center-of-pressure position; M = 1.97.Figure 2.- Concluded. 42Provided by IHSNot for ResaleNo reproduction or networking permitted without license from

5、 IHS-,-,-20 NACARM A54D19.I 1 Io .2 4 .6 .8 1.0Iocbtion, yis(a) Span loading.20 0=1.6- 1 /“ M:I,45 Z Mcf.97y 7Y.-“g 1,2 / 1/-/g/g .8% A . LinearTheory # d/- Experimental datar- 1press. forceO R =44xiO M= 1.45.68“M= 1.97.Figure 5.- Concluded.Provided by IHSNot for ResaleNo reproduction or networking

6、permitted without license from IHS-,-,-26 NACA RM A54D19C“:08765432I0 .2 .4 ,6 .8 1.0.Spanwiseo .2 .4 .6 ,8 1.0location, y/s(a) Span loading.-.!.0.6a)o0 .2wo .8I Linear theory -.z Experimental data;o“ 5 10 15 20 25 30 35 40 45 50 55Angle of attock, a,degt T(b) Normal-force cirves.Figure 6.- Aerodyna

7、mic characteristics of wing .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.NACA RM A54D19(c) Center-of-pressure position;.M = 1.45.27- 40 42 44 46 48.50Spanwise location, /s(d) Center-of-pressure Position; M=l.97.Figure 6.- Concluded.NACA-Langley -6-26-54- 926Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-