Heat flow measurements on high-speed aircraft modelsстатья
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Дата последнего поиска статьи во внешних источниках: 4 июня 2021 г.
Аннотация:The functionality of "Hypersonic aerodynamic shock tube" facility was expanded toobtain more complete validation of developed computer codes for the prospective high-speedaircraft aerothermodynamics description. The method of luminescent temperature converterswas applied in the laboratory installation. Measuring of temperature fields on the surface ofmodels installed in the aerodynamic unit when they have ambient air flow at Mach numbersM=5-7, have been implemented. The calorimetric type heat flow sensor was selected amongexisting heat flow sensors as it based on microsecond inertia, miniaturization, and relative easeof manufacturing. The sensitive elements of the calorimetric sensors were manufactured for thelaboratory installation. The ability of the manufactured sensors to work and the dependence ofthe response time from the thickness of the heat-receiving surface were revealed.