Experimental investigation of supersonic laminar, two-dimensional boundary-layer separation in a compression corner with and without cooling.
- 1 January 1968
- journal article
- research article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 6 (1), 7-14
- https://doi.org/10.2514/3.4434
Abstract
No abstract availableKeywords
This publication has 7 references indexed in Scilit:
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- Supersonic separated and reattaching laminar flows. i - general theory and application to adiabatic boundary-layershock-wave interactionsAIAA Journal, 1964
- Mach 8 to 22 studies of flow separations due to deflected control surfacesAIAA Journal, 1964
- Some Experiments on Hypersonic Separated FlowsARS Journal, 1962
- The Effects of Heat Transfer on Laminar-Boundary-Layer Separation in Supersonic FlowAeronautical Quarterly, 1961
- An Experimental Investigation of Leading-Edge Shock-Wave - Boundary-Layer Interaction at Mach 5.8Journal of the Aeronautical Sciences, 1957
- An experimental investigation of heat transfer effects on boundary layer separation in supersonic flowJournal of Fluid Mechanics, 1957