Flowfield Analysis for Successive Oblique Shock Wave-Turbulent Boundary-Layer Interactions
Open Access
- 1 January 1974
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Aircraft
- Vol. 11 (1) , 54-59
- https://doi.org/10.2514/3.60321
Abstract
No abstract availableKeywords
This publication has 5 references indexed in Scilit:
- A modified wall wake velocity profile for turbulent compressible boundary layers.Journal of Aircraft, 1973
- Combined Viscous-Inviscid Analysis of Supersonic Inlet FlowfieldsJournal of Aircraft, 1972
- Use of Coles' universal wake function for compressible turbulent boundary layersJournal of Aircraft, 1970
- Shock-wave reflection from a turbulent boundary layer with mass bleed.Journal of Aircraft, 1968
- The prediction of turbulent boundary layer development in compressible flowJournal of Fluid Mechanics, 1968