Preliminary experimental results of heat flux surface field registration at the hypersonic aerodynamic shock tube using temperature sensitive paint

Abstract

The temperature gradient fields of a wedge with double ramp were explored by using applied method temperature sensitive paint [1-4]. The model was studied experimentally in the HAST facility [5-8] at incoming airflow Mach numbers of M = 5...7. With the technique, perturbations of luminescent elements on the model surface during stationary hypersonic flow were recorded. The results of experimental data processing of surface temperature gradient fields are presented.