Hypersonic viscous shock layer on sweptback wings of infinite span at different angles of attack-Reference-Cited by-同舟云学术

Hypersonic viscous shock layer on sweptback wings of infinite span at different angles of attack

Published:1979 Issue:2 Volume:14 Page:238-246
ISSN:0015-4628
Container-title:Fluid Dynamics
language:en
Short-container-title:Fluid Dyn

Author:

Brykina I. G.,Gershbein �. A.

Publisher

Springer Science and Business Media LLC

Subject

Fluid Flow and Transfer Processes,General Physics and Astronomy,Mechanical Engineering

Link

http://link.springer.com/content/pdf/10.1007/BF01051666.pdf

Reference13 articles.

1. L. I. Sedov, M. P. Mikhailova, and G. G. Chernyi, ?Influence of viscosity and thermal conductivity on gas flow behind a strongly curved shock wave,? Vestn. Mosk. Univ. Ser. Fiz. Mat. Estest. Nauk, No. 3 (1953).

2. H. K. Cheng, ?The blunt-body problem in hypersonic flow at low Reynolds number,? Inst. Aerospace Sci. Paper, No. 92 (1963).

3. A. L. Ankudinov, ?Calculation of a viscous hypersonic shock layer with mass injection at moderately low Reynolds numbers,? Izv. Akad. Nauk SSSR, Mekh. Zhidk. Gaza, No. 3 (1970).

4. A. L. Ankudinov, ?Viscous shock layer around a paraboloid of revolution,? Tr. TsAGI, No. 1448 (1973).

5. K. M. Magomedov, ?Hypersonic flow of a viscous gas over blunt bodies,? Izv. Akad. Nauk SSSR, Mekh. Zhidk. Gaza, No. 2 (1970).

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2. Investigation of stationary flow of viscous gas in a thin three-dimensional shock layer;Fluid Dynamics;1980-09

3. Laminar boundary layer on swept-back wings of infinite span at an angle of attack;Fluid Dynamics;1980