Nonequilibrium hypersonic flow of gas past a wing of small aspect ratio

DOI10.1007/BF01090751zbMath0561.76069MaRDI QIDQ2266644

V. N. Golubkin, A. I. Golubinskij

Publication date: 1983

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

zbMATH Keywords

small aspect ratiothin shock layer methodconservation of vorticity along streamlinesflow of gas past a wingthree-dimensional nonequilibrium shock layer

Mathematics Subject Classification ID

Gas dynamics (general theory) (76N15) Hypersonic flows (76K05)

Related Items (1)

Optimum lifting body shapes in hypersonic flow at high angles of attack

Cites Work

• Hypersonic non-equilibrium flow over slender bodies
• LIFT OF SLENDER DELTA WINGS ACCORDING TO NEWTONIAN THEORY
• Unnamed Item

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