NASA NACA-TM-1105-1946 Plane and Three-Dimensional Flow at High Subsonic Speeds《在高亚音速下的飞机和三维流动》.pdf

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1、? c I I I /- I AT1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Y I k Y I (Zxtenaicx of the PraxIi1 Rule) 3y E. Scthsrt, 3erlin-ulersilcf Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 I 1 Provi

2、ded by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3 L pi i. I. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TI4 No. 1105 t Provided by IHSNot for ResaleNo reproduction or networking permitted without

3、 license from IHS-,-,-1. I I 5 P 2 Trr x bC i tiiht is, fr, tke coqreszible floa the $resexre ratio Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6 T;SACfl TM No, 1105 Provided by IHSNot for ResaleNo reproduction or networking permitted without lic

4、ense from IHS-,-,-c Veloclty lii_st-xrbance at a Great Distance frm the Airfoil in ircc-l)res;ible flow t5e vz1ocit-J prturbation et 8 ,r:-est distsncs froir? P slepder ring of large span is: Accor5i?q to a calc-Aation carrlied out in FB 1167 , Av,/v, Provided by IHSNot for ResaleNo reproduction or

5、networking permitted without license from IHS-,-,-0 1JA.CA TM No. llC5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-F . 9 AcsorCin!: to a c;lcaiz.tion cei-rfed out in FE 1165, the velocitg perturbatim CVJV ai a hrge distame frola 6 slender torig u

6、f revclutlcr, is, in ix;co:npressible f IQW : Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-10 NACA TM ?To. 1105, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-11 Provided by IHSNot for ResaleNo r

7、eproduction or networking permitted without license from IHS-,-,-12 NACA TM NO. 1105 1+ _. . 1 * : -. . . . . 1 - I” * Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I Provided by IHSNot for ResaleNo reproduction or networking permitted without lice

8、nse from IHS-,-,-1)_c NACA TM NO. 1105 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I . ITACA TPI NO. 1105 15 I I * Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I I 1 I NACA TM No. 1105 Figs. 1,

9、2 0 4 42 43 44 45 46 0.7 Fig, 1 Maximum super-stream velocity for elliptical cylinders and ellipsoids of revolution. t . Fig. 2 -Distance from profile-center line y/r Perturbation velocities for X=O through a plane and through rotationally symmetric disposition of source- depressions in incomDressib

10、le and compressible flow. ( Mach number M=O,8 1. Notation of coordinates: Perturbation velocity in Perturbation velocity in ( M=0,8 1 : (A V,/ V,)iC (A Vx/ Vok incompressible flow: compressible flow: Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fi

11、gs. 3,4 NACA TM No. 1105 Fig. 3 Maximum super-stream velocity and critical Mach number M* for elliptical cylinders and ellipsoids of revolution in symmetric flow. *o Mach number of the flow velocity at which the body attains sonic velocity. Fig. 4 The influence cf asrect ratio upon the increase of the lift coefficient at the same angle of attack by increa- sing the Mach number M I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-