Details of a Shock-Separated Turbulent Boundary Layer at a Compression Corner
- 1 December 1976
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 14 (12) , 1709-1715
- https://doi.org/10.2514/3.61513
Abstract
No abstract availableThis publication has 8 references indexed in Scilit:
- Shock wave-turbulent boundary layer interaction at a high Reynolds number, including separation and flowfield measurementsPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1976
- Incipient Separation of a Supersonic Turbulent Boundary Layer at High Reynolds NumbersAIAA Journal, 1976
- Incipient separation of a supersonic turbulent boundary layer at moderate to high Reynolds numbersPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1975
- Flowfield Measurements Using a Total Temperature Probe at Hypersonic SpeedsAIAA Journal, 1972
- Results of a strong interaction, wake-like model of supersonic separated and reattaching turbulent flowsAIAA Journal, 1971
- Separation of a supersonic turbulent boundary layer by a forward facing stepPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1971
- A reattachment criterion for turbulent supersonic separated flows.AIAA Journal, 1969
- Separation of a Supersonic Turbulent Boundary LayerJournal of the Aeronautical Sciences, 1955