Fluctuating wall pressures in a Mach 5 crossing shock/turbulent boundary layer interaction including asymmetric effects-Reference-Cited by-同舟云学术

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Fluctuating wall pressures in a Mach 5 crossing shock/turbulent boundary layer interaction including asymmetric effects

Published:1996-01-15 Issue: Volume: Page:
ISSN:
Container-title:34th Aerospace Sciences Meeting and Exhibit
language:
Short-container-title:

Author:

Tani Kouichiro¹,Dolling D.²

Affiliation:

1. National Aerospace Lab., Kakuda, Japan

2. Texas, Univ., Austin

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1996-45

Reference23 articles.

1. Mach 4 testing of scramjet inlet models

2. Ishiguro, T., Ogawa, S., Wada, W. "Numerical Calculation of Scramjet Inlet Flow," NAL Technical Report TR-1174T, 1992.

3. Fluctuating wall pressures near separation in highly swept turbulent interactions

4. a Single Strut," AIAA Paper 93-0741, AIAA <13) ^"les, G.S and Dolling, D.S., Swept

Cited by 3 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. Progress in shock wave/boundary layer interactions;Progress in Aerospace Sciences;2015-01

2. Progress in Shock Wave/Boundary Layer Interactions;43rd Fluid Dynamics Conference;2013-06-22

3. Scramjet Engine Research athe National Aerospace Laboratory in Japan;Scramjet Propulsion;2001-01-01

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