Unsteady viscous shock layer near the leading edge of a wing of infinite span

DOI10.1007/BF01051551zbMath0664.76079MaRDI QIDQ1115726

S. H. Smith

Publication date: 1988

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

zbMATH Keywords

second order approximationviscous shock layerwing of infinite spanNewtonian linearizationstagnation lineunsteady injectionwall temperature variation

Mathematics Subject Classification ID

Shock waves and blast waves in fluid mechanics (76L05) Transonic flows (76H05)

Cites Work

• Flow regimes of a viscous gas in a thin three-dimensional shock layer near a surface with small curvatures
• Viscous shock layer near the stagnation point on a rotating body with unsteady injection and surface cooling
• Investigation of stationary flow of viscous gas in a thin three- dimensional shock layer
• Numerical Solution of Supersonic Viscous Flow over Blunt Delta Wings

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