Navier-Stokes Solutions with Finite Rate Ablation for Planetary Mission Earth Reentries
Author:
Affiliation:
1. NASA Ames Research Center, Moffett Field, California 94035-1000
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.12248
Reference26 articles.
1. Ablation and Thermal Response Program for Spacecraft Heatshield Analysis
2. 3Kays, W. M., and Crawford, M. E., Convective Heat and Mass Transfer, 2nd ed.McGraw-Hill, New York, 1980, pp.355-357.
3. Mars Pathfinder trajectory based heating and ablation calculations
4. Aerothermodynamics of the Stardust Sample Return Capsule
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