Features of Afterbody Radiative Heating for Earth Entry
Author:
Affiliation:
1. NASA Langley Research Center, Hampton, Virginia 23681
2. ERC Inc., NASA Ames Research Center, Moffett Field, California 94035
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.A33084
Reference34 articles.
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3. Simulating Stardust Earth Reentry with Radiation Heat Transfer
4. OtsuH.SuzukiK.FujitaK.AbeT. “Assessment of Forebody and Backbody Radiative Heating Rate of Hypervelocity Reentry Capsule,” Inst. of Space and Astronautical Science, Rept. SP-17, 2003.
5. LiuY.PrabhuD.SoundersD.VinokurM.DateoC. “Comparison of Tangent Slab Approximation and Full Angular Integration in Computing Radiative Heating for the CEV Heatshield,” NASA TN/EG-CAP-06-124, 2006.
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