燃焼・圧力駆動衝撃風胴と二，三の平板熱伝達実験

Abstract

A combustion and/or pressure-driven shock tunnel with a conical nozzle is constructed. The tailoring Mach number MST of the combustion tumel is from 6.7 to 7.4. The heat transfer rate of sharp leading edge flat plates with a backward facing step in hypersonic flow of Mach number M∞=7.05 and 11.1 are measured by use of the pressure tunnel, and it is shown that the magnitude and the location of the peak heat transfer rate at reattachment region behind the step seem to be affected by the magnitude of M∞. The measured heat transfer rate of a sharp flat plate with angle of attack in M∞=11.1 hypersonic flow from the conical nozzle of the pressure tunnel is in qualitatively proper agreement with the author's analytical result. The behavior of the heat transfer rate near the sharp leading edge of anat plate in M∞=11.1·high stagnation temperature To=7, 900K flow measured by using the combustion tunnel shows tolerable agreement with the existing measured results at lower To in the strong viscous interactlon region.