Heat transfer to blunt-edged swept wings at angle of attack in hypersonic flow

DOI10.1007/BF02319081zbMath0856.76031OpenAlexW2074896139MaRDI QIDQ1815156

I. G. Brykina

Publication date: 7 November 1996

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

Full work available at URL: https://doi.org/10.1007/bf02319081

zbMATH Keywords

approximate analytic solutionviscous gascomparison with numerical solutions

Mathematics Subject Classification ID

Hypersonic flows (76K05)

Related Items (1)

Approximate analytical solutions for heat fluxes in three-dimensional hypersonic flow over blunt bodies

Cites Work

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• Approximate formulas for heat flows towards an ideally catalytic surface near a plane of symmetry
• Three-dimensional laminar boundary layer on a permeable surface in the neighborhood of a symmetry plane
• Supersonic laminar flow on the windward surface of yawed wings of infinite span over a broad range of Reynolds numbers
• Integration of hypersonic viscous shock layer equations by a successive approximation method

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