Optimal-contour design for a plane hypersonic engine output unit with account for the boundary layer, length, outer flow, and base end effects-Reference-Cited by-同舟云学术

Optimal-contour design for a plane hypersonic engine output unit with account for the boundary layer, length, outer flow, and base end effects

Published:2000-07 Issue:4 Volume:35 Page:612-619
ISSN:0015-4628
Container-title:Fluid Dynamics
language:en
Short-container-title:Fluid Dyn

Author:

Aukin M. K.,Tagirov R. K.

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/BF02698132.pdf

Reference6 articles.

1. M. K. Aukin and R. K. Tagirov, "Application of a direct method of determining the optimal contour of a supersonic jet engine output unit."Izv. Ross. Akad. Nauk, Mekh. Zhidk. Gaza, no. 1, 169 (1998).

2. V. S. Avduevskii, "Method of calculating the 3-D turbulent boundary layer in a compressible gas,"Izv. Akad. Nauk SSSR, Mekh. Mashinostr., no. 4, 3 (1962).

3. M. K. Aukin and R. K. Tagirov, "The calculation of the base pressure and the enthalpy behind a plane or axisymmetric step immersed in a supersonic flow with account for the entrance boundary layer effect,"Izv. Ross. Akad. Nauk, Mekh. Zhidk. Gaza. no. 2, 110 (1999).

4. M. K. Aukin nd R. K. Tagirov, "Second-order finite-difference scheme for calculating supersonic 3-D flows of inviscid gas,"Zh. Vych. Matem. Mat. Fiz.,29, no. 7, 1057 (1066).

5. B. Erahimi Houshang, "Parametric investigation of the effect of various phenomena on the performance of a scramjet nozzle,"AIAA Paper N95-6048 (1995).

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