Real-Gas and Surface-Ablation Effects on Hypersonic Boundary-Layer Instability over a Blunt Cone
Author:
Affiliation:
1. University of California, Los Angeles, Los Angeles, California 90049
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.J054404
Reference49 articles.
1. Ablation Thermal Protection Systems
2. CarterH.RaperJ.HinsonW.MorrisW. “Basic Measurements from a Turbulent-Heating Flight Experiment on a 5° Half-Angle Cone at Mach 20 (Reentry F),” NASA TM-X-2308, 1971.
3. JohnsonC.StainbackP.WickerK.BonyL. “Boundary-Layer Edge Conditions and Transition Reynolds Number Data for a Flight Test at Mach 20 (Reentry F),” NASA TM X-2584, 1972.
4. Payload optimization factors for storage of liquid hydrogen in a low-gravity environment
5. Effects of Roughness on Hypersonic Boundary-Layer Transition
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