Heat Transfer to Flat Plate in High Temperature Rarefied Ultrahigh Mach Number Flow
Author:
Affiliation:
1. General Electric Research Laboratory, Schenectady, N. Y.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Link
http://arc.aiaa.org/doi/pdf/10.2514/8.6059
Reference42 articles.
1. An Estimate of Viscosity Effect on the Hypersonic Flow Over an Insulated Wedge
2. Shock-Wave Effects on the Laminar Skin Friction of an Insulated Flat Plate at Hypersonic Speeds
3. On the Boundary-Layer Equations in Hypersonic Flow and Their Approximate Solutions
4. A Note on Hypersonic Viscous Flow over a Flat Plate
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2. NPARC simulation of scramjet inlet experiments at Mach numbers from 10-20;Space Plane and Hypersonic Systems and Technology Conference;1996-11-18
3. Experimental study of a two-dimensional scramjet at Mach numbers of 8 to 25;28th Aerospace Sciences Meeting;1990-01-08
4. Hypersonic scramjet inlet flow investigations, M1 = 16-26;27th Aerospace Sciences Meeting;1989-01-09
5. Relaminarization of the boundary layer over a flat plate in shock tube experiments;4th Thermophysics and Heat Transfer Conference;1986-06-02
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