A detailed study of attached and separated compression corner flowfields in high Reynolds number supersonic flow
- 10 July 1978
- conference paper
- Published by American Institute of Aeronautics and Astronautics (AIAA)
Abstract
No abstract availableThis publication has 5 references indexed in Scilit:
- Evaluation of turbulence models for three primary types of shock-separated boundary layersPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1977
- Mach 3 oblique shock wave/turbulent boundary layer interactions in three dimensionsPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1976
- Incipient Separation of a Supersonic Turbulent Boundary Layer at High Reynolds NumbersAIAA Journal, 1976
- Use of Coles' universal wake function for compressible turbulent boundary layersJournal of Aircraft, 1970
- Turbulent boundary-layer separation in front of a forward-facing step.AIAA Journal, 1967