ИСТИНА

The functionality of "Hypersonic aerodynamic shock tube" facility was expanded to obtain more complete validation of developed computer codes for the prospective high-speed aircraft aerothermodynamics description. The method of luminescent temperature converters was applied in the laboratory installation. Measuring of temperature fields on the surface of models installed in the aerodynamic unit when they have ambient air flow at Mach numbers M=5-7, have been implemented. The calorimetric type heat flow sensor was selected among existing heat flow sensors as it based on microsecond inertia, miniaturization, and relative ease of manufacturing. The sensitive elements of the calorimetric sensors were manufactured for the laboratory installation. The ability of the manufactured sensors to work and the dependence of the response time from the thickness of the heat-receiving surface were revealed.