Diffuser inlet flow structure following a shock-boundary layer interaction
- 1 April 1979
- proceedings article
- Published by American Institute of Aeronautics and Astronautics (AIAA)
Abstract
No abstract availableThis publication has 4 references indexed in Scilit:
- Diffusers for supersonic intakes - The dependence of conical diffuser performance on inlet flow conditionsPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1979
- Some Effects on Conical Diffuser Performance of Preceding Normal Shock Boundary-Layer InteractionProceedings of the Institution of Mechanical Engineers, 1974
- A Novel Low-Cost Diffuser for High-Performance Centrifugal CompressorsJournal of Engineering for Power, 1969
- An experimental investigation on the effect of subsonic inlet mach number on the performance of conical diffusersInternational Journal of Mechanical Sciences, 1966