Control of shock-wave boundary-layer interactions by bleed in supersonic mixed compression inlets-Reference-Cited by-同舟云学术

Control of shock-wave boundary-layer interactions by bleed in supersonic mixed compression inlets

Published:1975-08-16 Issue: Volume: Page:
ISSN:
Container-title:11th Propulsion Conference
language:
Short-container-title:

Author:

FUKUDA M.¹,RESHOTKO E.¹,HINGST W.²

Affiliation:

1. Case-Western-Reserve University, Cleveland, Ohio

2. NASA, Lewis Research Center, Cleveland, Ohio

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1975-1182

Reference11 articles.

1. Cubbison, R. W., Heleason. E.T. and Johnson, D.P. "Effect of.Porous Bleed in a High Performance Axismetric Mixed Compression Inlet at %ch 2.50". TM X-1692, 1968,NASA. mental Investigation of Boundary Layers in an Axisymetric,%ch 2.5, Mixed Compression Inlet". TM X-2902. 1973. NASA. cal and Experimental Performance of Two Isentropic Mixed Conpression Axisymetric Inlets at Mach Numbers 0.8 to 2.65". TN 0-7320, 1973, NASA.

2. Kilburg. R.P. and Kotansky. D.R. "Experimental Investigation of a Plane, Oblique Incident-Reflecting Shock Wave vith a Turbulent Boundary Layer on a Cooled Surface". CR-66841, 1969. SASA.

3. Arnold Ulgincering Development Center, 1961.

4. Performance estimates for a supersonic axisymmetric inlet system

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