An approximate viscous shock layer approach to calculating hypersonic flows about blunt-nosed bodies
Author:
Affiliation:
1. North Carolina State University, Raleigh
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1991-1348
Reference24 articles.
1. [l] J. D. Anderson, Jr. "A Survey of Modern Research in Hypersonic Aerodynamics". AIhA Paper 84-1578, June 1984.
2. [2]0.M. McWherter, R. W. Noack, and W. 1, Obcrkampf. "Evaluat,ioiiofInviscidlBoundary Layer and Paraboliacd Navier-Stokes Solutions for Design of Reentry Vehicles". AIAA Paper 84-0486,Jariuary 1984.
3. [3]P. A. Gnoffo. "An Upwind-Biased Point-Implicit Relaxation Algorithm for Viscous, Coinpressible Perfcct-Gas Flows". NASA TP 2953,Junc 1990.
4. [5]P. A. Gnoffo. "IIypersonic Flows Over Biconics Using a Variable-Effective-Gamma, Parabolized Navier Stokes Code". AlAA Paper 83-1666,July 1983.
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1. Approximate viscous shock layer technique for calculating hypersonic flows around blunt-nosed bodies;Journal of Spacecraft and Rockets;1994-07
2. Enhancements to viscous-shock-layer technique;Journal of Spacecraft and Rockets;1993-07
3. Enhancements to viscous-shock-layer technique;27th Thermophysics Conference;1992-07-06
4. Approximate Two Layer (Inviscid/Viscous) Methods to Model Aerothermodynamic Environments;Advances in Hypersonics;1992
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