Pressure Gradient Effects on Hypersonic Cavity Flow Heating

Author:

Everhart Joel1,Alter Stephen1,Merski Ronald1,Wood William1,Prabhu Ramadas2

Affiliation:

1. NASA Langley Research Center

2. Lockheed Martin Engineering & Sciences Co.

Publisher

American Institute of Aeronautics and Astronautics

Reference65 articles.

1. Blair, A.B., Jr. and Stallings, R.L., Jr. "Supersonic Axial-Force Characteristics of a Rectangular-Box Cavity with Various Length-to-Depth Ratios in aFlat Plate,"NASA TM-87659,1986.

2. Boerrigter, Herman and Charbonnier, Jean-Marc: "Roughness-induced transition in hypersonic flow," Space Scientific Research in Belgium,Volume4;51-52;D/1996/1191/5-Vol-4/(SEE 19970005230)

3. Buck, G.M., Powers, M.A., Nevins, S.C., Griffith, M.S., Verneris, P.H., and Wainwright, G.A. "Rapid Fabrication of Flat Plate Cavity Phosphor Thermography Test Models for Shuttle Return-to-Flight Aero-Heating," NASA/TM-2006 (Submitted for Publication).

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