Shock Wave/Boundary-Layer Interaction Control Using a Combination of Vortex Generators and Bleed-Reference-Cited by-同舟云学术

Shock Wave/Boundary-Layer Interaction Control Using a Combination of Vortex Generators and Bleed

Published:2013-05 Issue:5 Volume:51 Page:1221-1233
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Titchener Neil¹,Babinsky Holger¹

Affiliation:

1. Department of Engineering, University of Cambridge, Cambridge, England CB2 1PZ, United Kingdom

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/1.J052079

Reference34 articles.

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2. Survey of inlet development for supersonic aircraft

3. SurberL.TinappleJ. A. “Inlet Flow Control Technology: Learning from History, Reinventing the Future,” AIAA Paper 2012-0012, 2012.

4. OberyL.EnglertG.NussdorferT. “Pressure Recovery, Drag and Subcritical Stability Characteristics of Conical Supersonic Diffusers With Boundary-Layer Removal,” NACA RM-E51H29, 1952.

5. CampbellR. “Performance of a Supersonic Ramp Inlet with Internal Boundary-Layer Scoop,” NACA RM-E54I01, 1954.

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