Multi-Fidelity Approach to Estimate Heating for Three-Dimensional Hypersonic Aeroshells-Reference-Cited by-同舟云学术

Multi-Fidelity Approach to Estimate Heating for Three-Dimensional Hypersonic Aeroshells

Published:2013-07 Issue:4 Volume:50 Page:754-762
ISSN:0022-4650
Container-title:Journal of Spacecraft and Rockets
language:en
Short-container-title:Journal of Spacecraft and Rockets

Author:

Bopp Matthew S.¹,Ruffin Stephen M.¹,Braun Robert D.¹,Clark Ian G.¹,Theisinger John E.²

Affiliation:

1. School of Aerospace Engineering, Georgia Institute of Technology, Atlanta, Georgia 30332-0150

2. Atmospheric Flight and Entry Systems Branch, NASA Langley Research Center, Hampton, Virginia 23681

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.A32211

Reference24 articles.

1. Hypersonic and High-Temperature Gas Dynamics, Second Edition

2. Aerothermodynamic Shape Optimization of Hypersonic Entry Aeroshells

3. Axisymmetric analogy for three-dimensional viscous flow problems

4. BrykinaI. G.ScottC. D. “An Approximate Axisymmetric Viscous Shock Layer Aeroheating Method for Three-Dimensional Bodies,” NASA TM-98-207890, May 1998.

5. CookeJ. C. “An Axially Symmetric Analogue for General Three-Dimensional Boundary Layers,” British Aeronautical Research Council, Reports and Memoranda No. 3200, 1961.

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