Hypersonic Flow at a Mach Number of 10

Abstract

Tests designed to produce supersonic streams at ten and sixteen times the local speed of sound are described. In contrast to the usual wind tunnel apparatus, a conical nozzle is used for the expansion section, and the supply pressure is varied throughout a wide range. Some properties of the flow at high Mach numbers are discussed, and, in particular, data are given showing a systematic dependence of Mach number on stagnation pressures, a phenomenon not previously reported.