Progress in Flight Physics 2013
DOI: 10.1051/eucass/201305393
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Numerical analysis of dusty gas flow in a hypersonic shock tunnel

Abstract: The results of a computational simulation of an unsteady two-phase gas particle §ow in a hypersonic shock tunnel with a convergent-divergent nozzle are described. In calculations, the con¦guration of the tunnel and the initial gas and particles£ parameters were taken the same as in experiments carried out at the Central AeroHydroDynamic Institute (TsAGI) (Russia). The designed Mach number at the nozzle exit is M = 6.01. Particles are injected into the high-pressure chamber of the shock tube just before the dia… Show more

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