Institute of Space and Aeronautical Science University of Tokyo
Institute of Space and Aeronautical Science University of Tokyo
Institute of Space and Aeronautical Science University of Tokyo
In order to investigate structure and growth rate of vortex wake behind body of revolution at large angle of attack in supersonic flow, a series of wind tunnel experiments has been conducted using models with fineness ratio 10 at Mach number 2, Reynolds number around 3×10^5 and angle of attack, α, ranging from 0° to 35°. The results of experiments indicate that the vortex wake consists generally of the following two parts. The fore part, in which a pair of vortices grow up near the body surface, is relatively thin, the gradient of its outer boundary β=2～3°. The rear part grows up at the gradient β=α/2, in which the effect of the feeding sheet is comparable with that of the main two vortices. For the angle of attack α>20°,the growth of the vortices is so rapid that the fore part becomes very small, the rear part with the large gradient occupying the larger part of the vortex wake. Also a periodical motion of vortices becomes to be observed downstream in the vortex wake.
飛しょう体の渦後流についての実験的研究
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