Application of pulse tube for the test of the engines of hypersonic aircraft

Abstract

At M/sub H/=10, 12.2; T/sub OH/=2400 K, P/sub OH/=300-400 MPa in the hot-short aerodynamic tunnel, investigations of operating processes in the engine path of the scramjet model were performed. The model has rather simple external configuration. The inner channels are those ones which allow the burning of gaseous hydrogen as in sub- and super-sonic flows. Quantitative data on the distribution of pressure in the engine path were obtained. The experiments were performed in the IT-302M wind tunnel.