The effects of sidewall boundary layers in two-dimensional subsonic and transonic wind tunnels-Reference-Cited by-同舟云学术

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The effects of sidewall boundary layers in two-dimensional subsonic and transonic wind tunnels

Published:1981-06-23 Issue: Volume: Page:
ISSN:
Container-title:14th Fluid and Plasma Dynamics Conference
language:
Short-container-title:

Author:

SEWALL W.¹

Affiliation:

1. NASA, Langley Research Center, Transonic Aerodynamics Branch, Hampton, VA

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1981-1297

Reference11 articles.

1. Interactions between shock waves and turbulent boundary layers

2. 3Liepmann, H. W.; and Roshko, A, Elements of Gas Dynamics. John Wiley and Sons, Inc., c.1957, pp.256-258.

3. 4Ladson, Charles L.: Description and Calibration of the Langley 6- by 19-inch Transonic Tunnel. NASA TN 0-7182,1973.

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

2. A new facility and technique for two-dimensional aerodynamic testing;Journal of Aircraft;1983-06

3. A review of Reynolds number studies conducted in the Langley 0.3-m Transonic Cryogenic Tunnel;3rd Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference;1982-06-07

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