Boundary Layer Transition on Blunt Bodies in Hypersonic Flow
Interim scientific rept. Dec 1973-May 1974
VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM)
Pagination or Media Count:
Heat transfer and pressure distributions have been measured on a family of smooth and rough 50 deg - 8 deg biconic models in the M15 to 20, Re ft 2 million to 8.5 million flow simulating re-entry flow and achieved in the von Karman Institutes Longshot facility. The test conditions were selected to generate boundary layer transition data on these models.
- Fluid Mechanics
- Spacecraft Trajectories and Reentry