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Zhurnal Vychislitel'noi Matematiki i Matematicheskoi Fiziki, 2009, Volume 49, Number 9, Pages 1697–1707 (Mi zvmmf4761)  
This article is cited in 1 scientific paper (total in 1 paper)

Numerical study of the viscous hypersonic flow over a blunt delta wing

A. B. Gorshkov

Central Research Institute of Machine Building, ul. Pionerskaya 4, Korolev, Moscow oblast, 141070, Russia
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Abstract: A previously developed two-dimensional Navier–Stokes solver is extended to three dimensions. The hypersonic steady flow of an perfect gas (with a constant adiabatic index) over a delta wing with a spherical nose and a cylindrical leading edge is computed as an example. The characteristic features of the flow are analyzed. Pressure, heat flux, and friction coefficient distributions are computed in the shock layer and on the wing surface. The results are compared with available numerical and experimental data.
Key words: hypersonic flow, delta wing, perfect gas, Navier–Stokes equations, numerical simulation.
Received: 26.10.2007
English version:
Computational Mathematics and Mathematical Physics, 2009, Volume 49, Issue 9, Pages 1622–1631
DOI: https://doi.org/10.1134/S0965542509090164
Bibliographic databases:
Document Type: Article
UDC: 519.634
Language: Russian
Citation: A. B. Gorshkov, “Numerical study of the viscous hypersonic flow over a blunt delta wing”, Zh. Vychisl. Mat. Mat. Fiz., 49:9 (2009), 1697–1707; Comput. Math. Math. Phys., 49:9 (2009), 1622–1631
Citation in format AMSBIB
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    • This publication is cited in the following 1 articles:
    Citing articles in Google Scholar: Russian citations, English citations
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