Cylindrical and conical upstream influence regimes of 3D shock/turbulent boundary layer interactions
- 7 June 1982
- conference paper
- Published by American Institute of Aeronautics and Astronautics (AIAA)
Abstract
No abstract availableThis publication has 10 references indexed in Scilit:
- Flow visualization of separated 3D shock wave/turbulent boundary layer interactionsPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1982
- Scaling of interactions of cylinders with supersonic turbulent boundary layersAIAA Journal, 1981
- Upstream influence scaling of 2D and 3D shock/turbulent boundary layer interactions at compression cornersPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1981
- Upstream influence scaling of sharp fin-induced shock wave turbulent boundary layer interactionsPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1981
- Investigation of Three-Dimensional Shock/Boundary-Layer Interactions at Swept Compression CornersAIAA Journal, 1980
- A two-layer calculation for the initial interaction region of an unseparated supersonic turbulent boundary layer with a rampPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1980
- Analysis of Two-Dimensional Interactions Between Shock Waves and Boundary LayersAnnual Review of Fluid Mechanics, 1980
- The Flow Over a “High” Aspect Ratio Gothic Wing at Supersonic SpeedsAeronautical Quarterly, 1975
- Sweepback Effects in Turbulent Boundary-Layer Shock-Wave InteractionJournal of the Aerospace Sciences, 1960
- CX. The shock strength in supersonic “conical fields.”Journal of Computers in Education, 1949