NASA NACA-TN-2360-1951 Effect of tail surfaces on the base drag of a body of revolution at Mach numbers of 1 5 and 2 0《当马赫数为1 5和2 0时 尾翼面对回转体底部阻力的影响》.pdf

《NASA NACA-TN-2360-1951 Effect of tail surfaces on the base drag of a body of revolution at Mach numbers of 1 5 and 2 0《当马赫数为1 5和2 0时 尾翼面对回转体底部阻力的影响》.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-TN-2360-1951 Effect of tail surfaces on the base drag of a body of revolution at Mach numbers of 1 5 and 2 0《当马赫数为1 5和2 0时 尾翼面对回转体底部阻力的影响》.pdf（28页珍藏版）》请在麦多课文档分享上搜索。

1、GOVT.DOC._Dl“:_ E_qoqoRS%tVOXchange in base-pressure coefficient due to tail surfaces(Pbtail on-Pbtail off)free-stream dynamic pressureReynolds n_nber / Trailing _/_/ _S/_slw/_/w shock wave- ._:“_“_-I_C-_,_. _ _-_ _ _Boundory of _ _ dead-airFigure 4.-Sketch of simplified flow field in the neighbor-h

2、ood of the bose of o body- foil combination.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-,1/,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN 2360 21-4Toil Iocotion, x/cO 1.0 0.60 O.2A -0.2-

3、0.6in - 1.0r_ Toil offl0 I 2 3 4 x I0 _Reynolds number, R(o) M- /.5Figure 5.- Voriotion of bose- pressure coefficient with Reynoldsnumber; cruciform toil, tic - 0.10, roughness odded tobody.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-22 NACA TN 2

4、36OToil location, x/ce 1.0o OE02-02-0.6(1 - 1,0Toil offv,80 10 I 2 3 4 x 10 6 4FReynolds number, R(b) M = 2.0Figure 5.- Concluded.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-_CA _ 236O 23Tail thickness Simplifiedratio, /c analysiso 0.05 0.I0“ Plo

5、netoil LI-,I _ 0 _,. _ Cru ,for to/.I | ,-.2 =8 .4 0 -.4 -8Distance of toil trolling edge forward of bose, xtail chord c(o) M-I.5Figure 6.- Change in bose-pressure coefficient as o function of lolllocal/on.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-

6、,-,-24-.I._ 0_ _ “-,ITail thickness Simplifiedratio, tic analysiso 005 0.10Plane fail_ACA_ 2360.ICruciform tail/ /,“ I 1 I.8 .4 0 -4 -8D/s/once of toil /roilin_l eddie forward of bose , xfail chord c(b) M= 2.0Figure 6.- Concluded.Provided by IHSNot for ResaleNo reproduction or networking permitted w

7、ithout license from IHS-,-,-4 NACA _ 236O 25IIl /./I !IIr/!/I“ Ilue/_/Hoo_ e,/ns_e_d-eso_“: I_.NACA-Langley - 4-27-51 - 1000Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Y,fProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-