Mach 6 Experiments of Transition on a Cone at Angle of Attack
- 1 September 1982
- journal article
- research article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Spacecraft and Rockets
- Vol. 19 (5) , 397-403
- https://doi.org/10.2514/3.62276
Abstract
No abstract availableThis publication has 5 references indexed in Scilit:
- Effect of bluntness and angle of attack on boundary layer transition on cones and biconic configurationsPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1979
- Aerodynamic Calibration of the Aerospace Research Laboratories' M=6 High Reynolds Number FacilityPublished by Defense Technical Information Center (DTIC) ,1975
- 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 6Published by American Institute of Aeronautics and Astronautics (AIAA) ,1972
- Three-dimensional laminar boundary-layer transition on a sharp 8 degcone at Mach 10AIAA Journal, 1970
- Shock tunnel investigation of boundary-layer transition at M equals 5.5.AIAA Journal, 1967