Numerical Simulation of Nose Bluntness Effects on Hypersonic Boundary Layer Receptivity to Freestream Disturbances
Author:
Affiliation:
1. University of California, Los Angeles
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2011-3079
Reference29 articles.
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3. Stetson, K.F., Rushton, G. H., Shock Tunnel Investigation of Boundary-Layer Transition at M = 5.5. AIAA JOURNAL,1967.5(5):p.899-906.
4. Stetson, K.F., Thompson, E. R., Donaldson, J. C., and Siler, L. G., Laminar Boundary Layer Stability ExperimentsonaConeatMach8, Part2:BluntCone.AIAApaper1984-0006,1984.
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