Experimental Studies of Transitional Boundary Layer Shock Wave Interactions-Reference-Cited by-同舟云学术

Experimental Studies of Transitional Boundary Layer Shock Wave Interactions

Published:2006-01-09 Issue: Volume: Page:
ISSN:
Container-title:44th AIAA Aerospace Sciences Meeting and Exhibit
language:
Short-container-title:

Author:

Murphree Zachary¹,Jagodzinski J¹,Hood Egbert¹,Clemens Noel¹,Dolling David¹

Affiliation:

1. University of Texas at Austin

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2006-326

Reference6 articles.

1. 1Young, F.L., Kaufman, L.G., and Korkegi, R.H. "Experimental Investigation of the Interactions Between Blunt Fin Shock Waves and Adjacent BoundaryLayers at Mach Numbers 3 and 5,"ARL68-0214, Dec1968.

2. 2Hung, F.T. and Clauss J.M. "Three-Dimensional Protuberance Interference Heating in High-Speed Flow," AIAA-80-0289, AIAA18thAerospaceSciencesMeeting,Jan1980.

3. Supersonic Separated Flow past a Cylindrical Obstacle on a Flat Plate

4. 4Kaufman,L.G.,II,KorkegiR.H.andMorton,L.C."ShockImpingementCausedByBoundaryLayerSeparationAheadof BluntFins,"ARL72-0118, AerospaceResearch Laboratories, Wright-Patterson Air ForceBase, Ohio, Aug1972.

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