Modeling of Heat Transfer Attenuation by Ablative Gases During the Stardust Reentry
Author:
Affiliation:
1. Department of Mechanical Engineering, University of Kentucky, Lexington, Kentucky 40506
2. Department of Aerospace Engineering, University of Michigan, Ann Arbor, Michigan 48109
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.T4202
Reference42 articles.
1. Experimental and Numerical Study of Pyrolysis Gas Pressure in Ablating Test Piece
2. An Approximate Ablative Thermal Protection System Sizing Tool for Entry System Design
3. Numerical Simulation of Ablation for Reentry Vehicles
4. One-Dimensional Ablation Using a Full Newton's Method and Finite Control Volume Procedure
5. Two-Dimensional Ablation, Thermal Response, and Sizing Program for Pyrolyzing Ablators
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