Using axisymmetric analogue along the streamlines for the solution of three-dimensional viscous shock layer equations of hypersonic equilibrium flow-Reference-Cited by-同舟云学术

Using axisymmetric analogue along the streamlines for the solution of three-dimensional viscous shock layer equations of hypersonic equilibrium flow

Published:2008-07 Issue:6 Volume:22 Page:429-436
ISSN:1061-8562
Container-title:International Journal of Computational Fluid Dynamics
language:en
Short-container-title:International Journal of Computational Fluid Dynamics

Author:

Noori S.,Karimian S.M.H.

Publisher

Informa UK Limited

Subject

Mechanical Engineering,Mechanics of Materials,Energy Engineering and Power Technology,Condensed Matter Physics,Aerospace Engineering,Computational Mechanics

Link

http://www.tandfonline.com/doi/pdf/10.1080/10618560802216297

Reference25 articles.

1. Comparison of Hypersonic Experiments and PNS Predictions Part I: Aerothermodynamics

2. Blottner, F.G., Johnson, M., and Ellis, M., 1971. Chemically reacting viscous flow program for multi-component gas mixtures, Sandia Laboratories, Albuquerque, NM, Rept. SC-RR-70-754, December.

3. Cebeci, T. and Smith, A.M.O. 1974.Analysis of turbulent boundary layers, 215–217. New York: Academic press. 256, 264

4. Cheatwood, F.M. and DeJamentte, F.R., 1991. An approximate viscous shock-layer technique for calculating chemically reacting hypersonic flows about blunt nosed bodies, NASA CR-187617, August.

5. Approximate viscous shock layer technique for calculating hypersonic flows around blunt-nosed bodies

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