Calculation of Thermal Response of Ablator Under Arcjet Flow Condition
Author:
Affiliation:
1. Japan Aerospace Exploration Agency, Tokyo 182-0012, Japan
2. Nagoya University, Aichi 464-8603, Japan
3. Japan Aerospace Exploration Agency, Kanagawa 229-8510, Japan
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Condensed Matter Physics,Aerospace Engineering,Space and Planetary Science,Fluid Flow and Transfer Processes,Mechanical Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.25499
Reference26 articles.
1. Response of Heatshield Material at Stagnation Point of Pioneer-Venus Probes
2. Unified Calculation of Hypersonic Flowfield for a Reentry Vehicle
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