Flow features of shock-induced combustion around projectile traveling at hypervelocities
Author:
Affiliation:
1. Institute of Space and Astronautical Science, Sagamihara, Kanagawa 229, Japan
2. Nagoya University, Nagoya, Aichi 464-01, Japan
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Reference18 articles.
1. Flux-vector splitting calculation of nonequilibrium hydrogen-air reactions
2. Modeling supersonic combustion using a fully implicit numerical method
3. Numerical simulation of hypervelocity projectiles in detonable gases
4. Mechanism of Instabilities of Exothermic Hypersonic Blunt-Body Flows
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