Bulletin of the Korean Space Science Society (한국우주과학회:학술대회논문집(한국우주과학회보))

The Korean Space Science Society (한국우주과학회)
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SHOCK WAVE BOUNDARY LAYER INTERACTION STUDIES IN CORNER FLOWS

  • Lee Hee-Joon (Control Systems Group, Korea Aerospace Research Institute) ;
  • Vos Jan B. (Department of Mechanical Engineering, Ecole Poly technique Federale de Lausanne)
  • Published : 2004.10.01
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Abstract

Shock wave boundary layer interactions can make flows around a vehicle be very high pressure and temperature due to pass shock waves in small areas of the hypersonic vehicle. These phenomena can affect a critical problem in the design of hypersonic vehicles. To research the effect of shock wave boundary layer interactions, comer flows were studied in this paper using numerical studies with the NSMB (Navier-Stokes Multi Block) solver and then comparing corresponding numerical results with experimental data of the Huston High Speed Flow Field Workshop II. The mach number of flows is 12.3 in comer flows. The comparison with the computational result is presented based on diverse numerical schemes. Good agreement is obtained.

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