A novel approach for analyzing supersonic high Reynolds number flowswith separation-Reference-Cited by-同舟云学术

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A novel approach for analyzing supersonic high Reynolds number flowswith separation

Published:1990-01-08 Issue: Volume: Page:
ISSN:
Container-title:28th Aerospace Sciences Meeting
language:
Short-container-title:

Author:

POWER GREG¹

Affiliation:

1. United Technologies Research Center, East Hartford, CT

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1990-764

Reference39 articles.

1. [I] Ackeeret, J., Feldmanu, F. Rott, N. "Investigation of Compression Shocksand Boundary Layersin Gases hloving at High Speeds," Translated in NACA TN 1113from E.T.H Ziirich, No. 10,(1946), 194i.

2. [Z]Hakkinen, R.J., Greber, I., Trilling, L., and Aharbanel, S.S. "The Interaction of an Oblique Shock Wave with a Laminar Boundary Layer,' NASA Memo 218-59M: 1959.

Cited by 2 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. Computation of supersonic flows with embedded separated regions using an efficient PNS algorithm;13th Computational Fluid Dynamics Conference;1997-06-29

2. Numerical modeling of supersonic-flow deceleration in a two-dimensional duct in combustion of wall tangential hydrogen jets;Combustion, Explosion, and Shock Waves;1996-07

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