Experimental investigation of the effects of nose bluntness, free-stream unit Reynolds number, and angle of attack on cone boundary layer transition at a Mach number of 6
- 17 January 1972
- proceedings article
- Published by American Institute of Aeronautics and Astronautics (AIAA)
Abstract
No abstract availableThis publication has 7 references indexed in Scilit:
- Influence of Asymmetric Transition on Re-Entry Vehicle CharacteristicsJournal of Spacecraft and Rockets, 1971
- Boundary layer transition on hypersonic blunt, slender conesPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1969
- Shock tunnel investigation of boundary-layer transition at M equals 5.5.AIAA Journal, 1967
- Laminar boundary-layer growth on slightly blunted cones at hypersonic speedsJournal of Spacecraft and Rockets, 1965
- Shock curvature effect on the outer edge conditions of a laminar boundary layerAIAA Journal, 1963
- BOUNDARY CONDITIONS AT THE OUTER EDGE OF THE BOUNDARY LAYER ON BLUNTED CONICAL BODIESAIAA Journal, 1963
- Effects of slight nose bluntness and roughness on boundary-layer transition in supersonic flowsJournal of Fluid Mechanics, 1962