Boundary-layer displacement and leading-edge bluntness effects on attached and separated laminar boundary layers in a compression corner. II - Experimental study
- 1 January 1971
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 9 (1) , 84-93
- https://doi.org/10.2514/3.6127
Abstract
No abstract availableThis publication has 7 references indexed in Scilit:
- Experimental investigation of supersonic laminar, two-dimensional boundary-layer separation in a compression corner with and without cooling.AIAA Journal, 1968
- Prediction of incipient separation in shock- boundary-layer interactions.AIAA Journal, 1967
- On the Existence of a Pressure Plateau in Pure Laminar Separated FlowsAIAA Journal, 1966
- Experimental studies of separated flows at hypersonic speeds. II - Two-dimensional wedge separated flow studies.AIAA Journal, 1966
- MEASUREMENTS OF HEAT TRANSFER RATES IN SEPARATED REGIONS IN A SHOCK TUBE AND IN A SHOCK TUNNELAIAA Journal, 1963
- Some Experiments on Hypersonic Separated FlowsARS Journal, 1962
- Boundary-Layer Displacement and Leading-Edge Bluntness Effects in High-Temperature Hypersonic FlowJournal of the Aerospace Sciences, 1961