Compressible laminar boundary layer on a delta wing with attached shock wave-Reference-Cited by-同舟云学术

Compressible laminar boundary layer on a delta wing with attached shock wave

Published:1986 Issue:5 Volume:26 Page:624-629
ISSN:0021-8944
Container-title:Journal of Applied Mechanics and Technical Physics
language:en
Short-container-title:J Appl Mech Tech Phys

Author:

Vetlutskii V. N.,Poplavskaya T. V.

Publisher

Springer Science and Business Media LLC

Subject

Mechanical Engineering,Mechanics of Materials,Condensed Matter Physics

Link

http://link.springer.com/content/pdf/10.1007/BF00915308.pdf

Reference21 articles.

1. B. M. Bulakh, Nonlinear Conical Flow of Gases [in Russian], Nauka, Moscow (1970).

2. G. G. Chernyi, ?Wings in hypersonic flow,? Prikl. Mat. Mekh.,29, No. 4 (1965).

3. A. P. Bazzhin and I. F. Chelysheva, ?Numerical solution to supersonic flow past plane delta wing at small angles of attack,? Uchen. Zap. Tsentral'nyi Aerogidrodinamicheskii Institut (TsAGI),5, No. 5 (1974).

4. V. A. Bashkin, ?Compressible laminar boundary layer in conical external flow,? Tr. TsAGI,1093 (1968).

5. A. N. Minailos, ?Supersonic flow past thin wings,? Uchen. Zap. TsAGI,8, No. 4 (1977).

Cited by 3 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Computational analysis of a spatial compressed turbulent boundary layer on the upwind side of delta wings under supersonic flow;Journal of Applied Mechanics and Technical Physics;1994-01

2. Numerical calculation of a three-dimensional laminar compressible boundary layer on profiled triangular wings with supersonic front edges;Journal of Applied Mechanics and Technical Physics;1994

3. Calculation of a laminar boundary layer on the leeward side of a triangular plate with supersonic leading edges;Journal of Applied Mechanics and Technical Physics;1989