Canonical Normal Shock Wave/Boundary-Layer Interaction Flows Relevant to External Compression Inlets-Reference-Cited by-同舟云学术

Canonical Normal Shock Wave/Boundary-Layer Interaction Flows Relevant to External Compression Inlets

Published:2013-09 Issue:9 Volume:51 Page:2208-2217
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Loth Eric¹,Titchener Neil²,Babinsky Holger²,Povinelli Louis³

Affiliation:

1. Mechanical and Aerospace Engineering, University of Virginia, Charlottesville, Virginia 22904

2. Fluid Mechanics, University of Cambridge, Cambridge, England CB2 1PZ, United Kingdom

3. Propulsion Systems Division, NASA John H. Glenn Research Center at Lewis Field, Cleveland, Ohio 44135

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/1.J052175

Reference54 articles.

1. OberyL. J.EnglertG.NussdorferT. “Pressure Recovery, Drag and Subcritical Stability Characteristics of Conical Supersonic Diffusers with Boundary-Layer Removal,” NACA RM-E51H29, Washington, D.C. 1952.

2. PiercyT. G.JohnsonH. W. “A Comparison of Several Systems of Boundary-Layer Removal Ahead of a Typical Conical External-Compression Side Inlet at Mach Numbers of 1.88 and 2.9,” NACA RM-E53F16, Washington, DC, 1953.

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

4. OberyL. J.CubbinsonR. “Effectiveness of Boundary-Layer Removal near Throat of Ramp-Type Side Inlet at Free-Stream Mach Number of 2.0,” NACA RM-E54I14, 1954.

5. BeheimM. A.GertsmaL. W. “Performance of Variable Two-Dimensional Inlet Designed for Engine-Inlet Matching I–Performance at Design Mach Number of 3.07,” NACA RM-E56H23, Washington, D.C. Nov. 1956.

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