Fin Leading-Edge Sweep Effect on Shock-Shock Interaction at Mach 6
Author:
Affiliation:
1. NASA Langley Research Center, Hampton, Virginia 23681-0001
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/2.3247
Reference20 articles.
1. ANOMALOUS HEAT TRANSFER AND PRESSURE DISTRIBUTIONS ON BLUNT BODIES AT HYPERSONIC SPEEDS IN THE PRESENCE OF AN IMPINGING SHOCK.
2. Measurements of heating in regions of shock/shock interaction in hypersonic flow
3. Exploratory study of heating due to a hypersonic, high-enthalpy shock/shock interaction
4. Monte Carlo simulation of a near-continuum shock-shock interaction problem
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