Local heat transfer, equilibrium temperatures, and pressure have been measured on a circular cylinder for yaw angles from 0° to 60° and Reynolds numbers from 1X106 to 4X106. Increasing the yaw angle from 0° to 40° generally caused large increases in local heat-transfer coefficients followed by a decrease as the yaw angle was increased to 60°. The level of heating rates and the type if chordwise distribution indicated that a flow mechanism different from the conventional transitional boundary layer may exist for the intermediate yaw angles.

Abstract: Temperature recovery factors were determined for a slender, thin-walled cone-cylinder, having a 12° vertex angle and a 1.25-inch-diameter cylinder, at Mach numbers from 3.02 to 6.30. The angle-of-attack range was 0° to 45° at Mach numbers up to 3.50, and about 0° to 20° at Mach numbers from 4.23 to 6.30. A transverse cylinder of the same diameter was also tested at Mach number 3.02. Free-stream Reynolds numbers varied from 1.8 to 11.0 million per foot. Flow visualization studies of boundary-layer transition and flow separation were made and the results correlated with recovery-factor measurements.

Aerodynamic-heat-transfer measurements have been made at a station on the 10 degree total angle conical nose of a rocket-propelled model at flight Mach numbers of 1.4 to 3.9. The corresponding values of local Reynolds number varied from 18,000,000 to 46,000,000 and the ratio of skin temperature to local static temperature varied from 1.2 to 2.4. The experimental data, reduced to Stanton number, were in fair agreement with values predicted by Van Driest's theory for heat transfer on a cone with turbulent flow from the nose tip.