An Experimental Investigation of Leading-Edge Shock-Wave - Boundary-Layer Interaction at Mach 5.8
- 1 January 1957
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of the Aeronautical Sciences
- Vol. 24 (1) , 47-56
- https://doi.org/10.2514/8.3763
Abstract
No abstract availableKeywords
This publication has 5 references indexed in Scilit:
- Viscous Flow Along a Flat Plate Moving at High Supersonic SpeedsJournal of the Aeronautical Sciences, 1956
- General Theory of High Speed AerodynamicsPublished by Walter de Gruyter GmbH ,1954
- Viscous and Leading-Edge Thickness Effects on the Pressures on the Surface of a Flat Plate in Hypersonic FlowJournal of the Aeronautical Sciences, 1954
- Shock-Wave Effects on the Laminar Skin Friction of an Insulated Flat Plate at Hypersonic SpeedsJournal of the Aeronautical Sciences, 1953
- On the Boundary-Layer Equations in Hypersonic Flow and Their Approximate SolutionsJournal of the Aeronautical Sciences, 1953