Preliminary Results on Heat Transfer to the Afterbody of the Apollo Reentry Configuration at a Mach Number of 8

Heat-transfer rates on the afterbody of the Apollo reentry configuration have been measured in a low-enthalpy wind tunnel at a Mach number of 8. The data have been presented as the ratio of the measured heat-transfer coefficient on the afterbody to the calculated heat-transfer coefficient at the stagnation point at zero angle of attack. This ratio was found to vary from a low of approximately 0.01 to a maximum of about 0.52 as the angle of attack varied from 0 to 55 deg.