WIND TUNNEL TESTS AT SUPERSONIC MACH NUMBERS TO DETERMINE HEAT-TRANSFER COEFFICIENTS IN THE SHOCK WAVE-BOUNDARY LAYER INTERACTION REGION ON A PLANE SURFACE

摘要

All of the reduced data from the investigation was forwarded to NAA at the conclusion of the tests. In this report only the heat transfer coefficient data from two typical runs is included, but complete sets of the reduced data may be obtained, if desired, by addressing a request to the Commander (Code N316), Naval Missile Center, Point Mugu, California.