Mach 3 wind tunnel test of mixed compression supersonic inlet
Author:
Affiliation:
1. National Aerospace Laboratory, Tokyo, Japan
2. Tokyo, Science University, Japan
3. Ishikawajima-Harima Heavy Industries Co., Ltd., Tokyo, Japan
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1992-3625
Reference2 articles.
1. Hypersonic turbomachinery-based air-breathing engines for the earth-to-orbit vehicle
2. Mass flow ratio (GIGc) Fig.15 Pressure recovery V.S. massflow ratiooftheModc1-2
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