Inviscid/Boundary-Layer Aeroheating Approach for Integrated Vehicle Design
Author:
Affiliation:
1. NASA Langley Research Center
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2017-1146
Reference39 articles.
1. The NASA Reusable Launch Vehicle Technology Program
2. Computational Aerothermodynamic Design Issues for Hypersonic Vehicles
3. Engineering Aerothermal Analysis for X-34 Thermal Protection System Design
4. Aerodynamic heating environment definition/thermal protection systemselection for the HL-20
5. Aeroheating Design Issues for Reusable Launch Vehicles -- A Perspective
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1. Surface Heat Flux Prediction using Euler equation with immersed boundary method and the reference temperature method;AIAA SCITECH 2024 Forum;2024-01-04
2. Development of a Rapid Inviscid/Boundary-Layer Aerodynamics Tool;22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference;2018-09-15
3. Improved Approximate Method for Computing Convective Heating on Hypersonic Vehicles;Journal of Aerospace Engineering;2018-09
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