Simulation of Bleed-Hole Rows for Supersonic Turbulent Boundary Layer Control-Reference-Cited by-同舟云学术

Simulation of Bleed-Hole Rows for Supersonic Turbulent Boundary Layer Control

Published:2008-01-07 Issue: Volume: Page:
ISSN:
Container-title:46th AIAA Aerospace Sciences Meeting and Exhibit
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Author:

Hamed Awatef¹,Li Zhisong¹

Affiliation:

1. University of Cincinnati

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2008-67

Reference19 articles.

1. 2Fujimoto, A., Niwa, N., and Sawada, K. "Numerical Investigation on Supersonic Inlet with Realistic Bleed and Bypass Systems,*' AIAAPaper 91-0127,Jan. 1991.

2. 3Fujimoto, A., and Niwa, N. "Experimental and Numerical Investigation of Mach 2.5 Supersonic Mixed Compression Inlet", AIAAPaper 93-0289,Jan.1993.

3. 4Saunders, J. D., and Keith, T. G., Jr. "Results from Computational Analysis of a Mixed Compression Supersonic Inlet," AIAA Paper91-2581, June1991.

4. 5Reddy, D. R., Benson, T. J., and Weir, L. J. "Comparison of 3-D Viscous Flow Computations of Mach 5 Inlet with Experimental Data," AIAAPaper 90-0600, Jan.1990.

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