Flow Mechanism in a Hypersonic Sidewall Compression Inlet with a Rectangular-to-Circular Isolator
Author:
Affiliation:
1. National University of Defense Technology, 410073 Changsha, People’s Republic of China
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.A33348
Reference17 articles.
1. Performance of an Inlet for an Integrated Scramjet Concept
2. HollandS. D. “Mach 10 Experimental Database of a Three-Dimensional Scramjet Inlet Flow Field,” NASA TM 4648, 1995.
3. Effects of body-side compression on forward-swept sidewall compression inlets
4. Review of the physics of swept-shock/boundary layer interactions
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