Concept of Non-Ablative Thermal Protection System for Hypersonic Vehicles
Author:
Affiliation:
1. State Key Laboratory of High-Temperature Gas Dynamics, Chinese Academy of Sciences, 100190 Beijing, People’s Republic of China
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.J051875
Reference27 articles.
1. AndersonJ. D., Hypersonic and High Temperature Gas Dynamics, McGraw-Hill, New York, 1989, p. 262.
2. Shock Wave Drag Reduction
3. CrawfordD. H. “Investigation of the Flow over a Spiked-Nose Hemisphere-Cylinder at a Mach Number of 6.8,” NASA TN-D118, 1959.
4. Unsteady Aerodynamic Considerations in the Design of a Drag-Reduction Spike
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