Numerical investigation of the hypersonic viscous shock layer on wings of infinite span at angles of attack and slip

DOI10.1007/BF01091249zbMath0549.76044OpenAlexW1991463776MaRDI QIDQ800158

È. A. Gershbeĭn, V. S. Shchelin, S. A. Yunitskiĭ

Publication date: 1984

Published in: Fluid Dynamics (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1007/bf01091249

zbMATH Keywords

implicit finite difference schemeRankine-Hugoniot relationsblowing-suction parameterflow past wingsrounded leading edge

Mathematics Subject Classification ID

Shock waves and blast waves in fluid mechanics (76L05) Hypersonic flows (76K05)

Related Items (3)

Investigation of a three-dimensional hypersonic viscous shock layer on blunt bodies around which flow occurs at angles of attack and slippage ⋮ A comparison of the models of a thin and a complete viscous shock layer in the problem of the supersonic flow of a viscous gas past blunt cones ⋮ On the theory of a three-dimensional, viscous hypersonic shock layer in the neighbourhood of the plane of symmetry

Cites Work

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