Interaction of a laminar hypersonic boundary layer and a corner expansion wave
- 20 January 1969
- proceedings article
- Published by American Institute of Aeronautics and Astronautics (AIAA)
Abstract
No abstract availableThis publication has 3 references indexed in Scilit:
- Shock-Induced Separation of a Laminar Boundary Layer in Supersonic Flow Past a Convex CornerAeronautical Quarterly, 1965
- Laminar, transitional, and turbulent heat transfer after a sharp convex cornerAIAA Journal, 1964
- Laminar Heat Transfer Over Blunt-Nosed Bodies at Hypersonic Flight SpeedsJournal of Jet Propulsion, 1956