In this work the experimental results of research of a plume structure at axial hydrogen injection in a supersonic high-temperature air jet are presented. Two levels of temperatures are compared. One of them (1500-2000 K) is usually achieved in the ground experimental facility with a long period of action. The other level of temperature (2500-2700 K) is characteristic for installations with a short period of action.

A theoretical and experimental investigation of mixing and supersonic combustion is presented. A review of the problem under investigation is given. Then an analysis of inviscid flow fields with a finite rate chemistry for a hydrogen-air reaction is presented, an an analysis of a turbulent mixing for flows with large density gradients with no chemical reaction is presented. The analysis is compared wit the experimental results. Results of the experiments in upersonic combustion are presented. (Author).