K. R. Czarnecki, Archibald R. Sinclair
An investigation has been made to determine the effect of heat transfer on the peak pressure rise associated with the separation of a turbulent boundary layer on a body of revolution (NACA RM-10) at a Mach number of 1.61. Tests were made over a Reynolds number range from 11.6 X 10 to the 6th to 34.8 X 10 to the 6th and with 0 to 120 degrees F of cooling, which corresponds to a ratio of model-wall temperature to stagnation temperature of 0.96 (zero heat transfer) to 0.75. The stagnation temperature was approximately 570 degrees F absolute. Boundary-layer separation was induced by means of forward-facing steps or collars at the base of the model and changes in heat transfer were obtained by cooling the model. The peak pressure rise was determined from shock angles measured from schlieren photographs.
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