Hypersonic similarity solutions for airfoils supporting exponential shock waves
Author:
Affiliation:
1. The RAND Corporation, Santa Monica, Calif.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.5661
Reference8 articles.
1. f t This corrects a statement in the first paragraph of Ref. 5. tt Ref. 1, p.108.
2. EFFECT OF SLIGHT LEADING EDGE BLUNTING ON HYPERSONIC FLOWS PAST BODIES
Cited by 11 articles. 订阅此论文施引文献 订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献
1. Energy Deposition ahead of Pointed Profiles with Attached Shock Waves: Perturbed Euler Similarity;15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference;2008-04-28
2. Perturbed-Euler Similarity Profiles Supporting Attached Shock Waves;14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference;2006-06-15
3. New similarity solutions for hypersonic boundary layers with applications to inlet flows;AIAA Journal;1995-11
4. Similarity solutions for hypersonic flow past slender bodies of revolution at small incidence;Acta Astronautica;1995-04
5. Supersonic flow past pointed-nose thin airfoils;Acta Astronautica;1992-05
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