A numerical study of viscous shock-on-shock hypersonic flows with a modified Steger-Warming flux split scheme
Author:
Affiliation:
1. USAF, Wright Research and Development Center, Wright-Patterson AFB, OH
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1990-1491
Reference45 articles.
1. J.A. White and C.M. Rhie. Numerical Analysis of Peak Heat Transfer Rates for Hypersonic Flow Over a Cowl Leading Edge. AIAA Paper 87-1895,
2. G.H. Klopfer and H.C. Yee. Viscous Hypersonic Shock-On-Shock Interaction on Blunt Cowl Lips. AIAA Paper 88-0233,1988.
3. B. Edney. Anomalous Heat Transfer and Pressure Distributions on Blunt Bodies at IIypersonic Speeds in the Presence of an Impinging Shock. Technical Report 115, The Aeronautical Research Institute of Sweden,Stockholm,February 1968.
4. A.R. Wieting and M.S. Holden. Experimental Study of Shock Wave Interference Heating on a Cylindrical Leading Edge at Mach 6 and 6. AIAA Paper 87-1511,1987.
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