Three-dimensional hypersonic shock wave/turbulent boundary-layer interactions
作者： M. I. Kussoy , K. C. Horstman
DOI: 10.2514/3.11310
关键词:
摘要: Experimental data for a series of three-dimensional shock wave/turbulent boundary-layer interaction flows at Mach 8.2 are presented. The test bodies, composed sharp fins fastened to flat plate surface, were designed generate with varying degrees pressure gradient, separation, and turning angle. include surface pressure, heat transfer, skin friction distributions as well limited mean flowfield surveys in both the undisturbed regimes. obtained purpose validating computational models these hypersonic interactions.
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jaxa.jp参考文章(6)
M. KUSSOY, K. HORSTMAN, K. KIM, An experimental study of a three-dimensional shock wave/turbulent boundary-layer interaction at a hypersonic Mach number 22nd Fluid Dynamics, Plasma Dynamics and Lasers Conference. ,(1991) , 10.2514/6.1991-1761
G. SETTLES, L. DODSON, Hypersonic Shock/Boundary-Layer Interaction Database 22nd Fluid Dynamics, Plasma Dynamics and Lasers Conference. ,(1991) , 10.2514/6.1991-1763
Gary S. Settles, Lori J. Dodson, Supersonic and hypersonic shock/boundary-layer interaction database AIAA Journal. ,vol. 32, pp. 1377- 1383 ,(1994) , 10.2514/3.12205
DOYLE KNIGHT, C. HORSTMAN, D. MONSON, The hypersonic shock wave-turbulent boundary layer interaction generated by a sharp fin at Mach 8.2 30th Aerospace Sciences Meeting and Exhibit. ,(1992) , 10.2514/6.1992-747
G. SETTLES, D. DOLLING, Swept shock/boundary-layer interactions - Tutorial and update 28th Aerospace Sciences Meeting. ,(1990) , 10.2514/6.1990-375
M. I. Kussoy, K. C. Horstman, Documentation of two- and three-dimensional shock-wave/turbulent-boundary-layer interaction flows at Mach 8.2 NASA Ames Research Center Technical Report. ,(1991)