Boundary-layer displacement and leading edge bluntness effects on attached and separated laminar boundary layers in a compression corner. I - Theoretical study
- 1 December 1970
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 8 (12) , 2179-2188
- https://doi.org/10.2514/3.6084
Abstract
No abstract availableThis publication has 7 references indexed in Scilit:
- On the hypersonic laminar near wake critical point of the Crocco-Lees mixing theoryPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1967
- Further results of viscous interaction theory for the laminar supersonic near wakePublished by American Institute of Aeronautics and Astronautics (AIAA) ,1967
- Experimental studies of separated flows at hypersonic speeds. II - Two-dimensional wedge separated flow studies.AIAA Journal, 1966
- Modified Crocco-Lees Mixing Theory for Supersonic Separated and Reattaching FlowsJournal of the Aerospace Sciences, 1962
- GENERAL METHOD OF INTEGRAL RELATIONS AND ITS APPLICATION TO BOUNDARY LAYER THEORYPublished by Elsevier ,1962
- On the Approximate Solution of the Laminar Boundary-Layer EquationsJournal of the Aeronautical Sciences, 1954
- A Mixing Theory for the Interaction Between Dissipative Flows and Nearly Isentropic StreamsJournal of the Aeronautical Sciences, 1952