NASA NACA-RM-A53L22-1954 An experimental investigation of four triangular-wing-body combinations in sideslip at Mach numbers 0 6 0 9 1 4 and 1 7《在马赫数为0 6 0 9 1 4和1 7时 侧滑中四个三角形机翼组合的.pdf

《NASA NACA-RM-A53L22-1954 An experimental investigation of four triangular-wing-body combinations in sideslip at Mach numbers 0 6 0 9 1 4 and 1 7《在马赫数为0 6 0 9 1 4和1 7时 侧滑中四个三角形机翼组合的.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-RM-A53L22-1954 An experimental investigation of four triangular-wing-body combinations in sideslip at Mach numbers 0 6 0 9 1 4 and 1 7《在马赫数为0 6 0 9 1 4和1 7时 侧滑中四个三角形机翼组合的.pdf（18页珍藏版）》请在麦多课文档分享上搜索。

1、RESEARCH MEMORANDUMAN EXPEENTAL INVESTIGATION OF FOURWING-BODY COMBINATIONS IN SIDESHPTRD.NGUU%AT MACHFfUMBEM 0.6, 0.9, 1.4, AND 1.7By Frederik B. ChristensenAmes Aeronautical LaboratoryMoffett Field, Calif.bh=.-)ClassiflcdisKe8fd (IXrti:wyc:3.R)Auth”Stfin -F-K F%.% h.b.m%= *i$(IFFI=AiJTHO1Z5DTO CUM

2、GE)6 fib- . - . :-.%bmlmzti.004.002 QNACA 0003-63QNACA 0005-63-.002-.004 !.002.00/ 6NACA 0003-63en o-.001-.002 -13.004 NACA 0003-63.002 NACA 0005-63Q Body alone (Ref2)c oA/ -.002 “ q ) “ Ga 49 -.004 .-J o .? .2 .3 .4 .5 .6 .7CL4.- Effect of thickness on the effective-dihedralparameter, Cz,the direct

3、ional-stabilitY l?arterj cnpCy, for a body in combition th Planeratio = 2; M = 1.4.and the side-force parameterstriangular wings; aspectProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-14 NACA R.MA53L22LL1,004 ,I Ill.002 h Combered and twisted0 Planeq

4、p ouiA 4b-.002 m v .7004.002I I.001 A Cambered and twistedG Planeco ,Ip- .00/ , a % d- h-.002 1 ?fi(a) M = 0.6Figure 5.- Effeet of carober and twist on thec2p the directional-stabilityparameter,eter, Cy , for a body in combinationwithratio = B, t/c = 0.03.effective-dihedralparameter,Cn$ and the side

5、-force parsm-triangularwings; aspect.,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM A53122 15.004A Cambered and f wisted.002 0 PlaneAc o-.002-.004.002II.00/ A Cambered and fwisted0 PlaneCnp o-.00/ &41-.002.004A Cambered and +wisted.002 0 Pf

6、aneQ Body alone (RefmcoYp-.002-.oof, o .1 .2 .3 .4 .5 .6 .7c(b) M = 0.9Figure 5.- Continued.“ y?=ww “ -*$.,a- . :Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACARMA53w2.004! I II !I I I I I.002 A Cambered and twistedO P/one-.002H-.0041 II 1 1 1 I

7、 1 I 1 I I I I I I I.002.00/ A Cambered and +w&iedO Plane-.00/“-.002.004”A Cambered and twisted.002Q Body alone (Ref&YCypo-,004 f-.f o .1 .2 .3 .4 .5 .6 .7(c) M :1.4Figure 5.- Continued.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3.NACA RM.004.00

8、2 A Cambered and twistedO PJane7002-.004.002.00/ A Cambered and twisted Plane-.00/-.002.004.002c% o-.002-.00:,A Cambered and twistedQ Body alone (Ref. O .1 .2 .3 .4 .5 .6 .7e(d) M = 1.7Figure 5.- Concluded.NACA-Lamgley - S-16-54 -326Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-