Effects of Pressure Gradient on Stability and Skin Friction in Laminar Boundary Layers in Compressible Fluids
Author:
Affiliation:
1. General Electric Company,
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Link
http://arc.aiaa.org/doi/pdf/10.2514/8.1947
Reference13 articles.
1. Stability of Boundary Layers and of Flow in Entrance Section of a Channel
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1. Stability of a hypersonic boundary layer with a pressure gradient;Doklady Physics;2000-04
2. Effect of pressure gradient on the stability of compressible boundary layers;AIAA Journal;1992-09
3. Laminar, transition, and turbulent boundary- layer characteristic with favorable pressure gradient M sub 1 equals 9.6;Journal of Aircraft;1971-03
4. Boundary-layer transition on sharp cones at hypersonic Mach numbers.;AIAA Journal;1968-03
5. Hypersonic laminar boundary-layer transition on 8-foot-long, 10 deg cone, M sub 1 equals 9.1-16.;AIAA Journal;1967-07
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