MEASUREMENTS OF HEAT TRANSFER AND BOUNDARY-LAYER TRANSITION ON AN 8-INCH-DIAMETERnHEMISPHERE-CYLINDER IN FREE FLIGHT FOR A MACH NUMBERnRANGE OF 2.00 TO 3.88

摘要

Measurements of aerodynamic neat transfer have been made along the hemisphere and cylinder of a hemisphere-cylinder rocket-propelled model in free flight up to a Mach number of 3.88. The test Reynolds number based on free-stream condition and diameter of model covered a range from 2.69 x 106 to 11.70 x 106.nLaminar, transitional, and turbulent heat-transfer coefficients were obtained. The laminar data along the body agreed with laminar theory for blunt bodies whereas the turbulent data along the cylinder were consistently lower than that predicted by the turbulent theory for a flat plate. Measurements of heat transfer at the stagnation point were, in general, lower than the theory for stagnation-point heat transfer. When the Reynolds number to the junction of the hemisphere-cylinder was greater than 6 x 10 , the transitional Reynolds number varied from 0.8 X 10° to 3.0 x 106;however, when the Reynolds number to the junction was less than 6 x 10 , the transitional Reynolds number varied from 7.0 x 106 to 24.7 X 106.