Abstract
Aerodynamic heating test of a HTV-R capsule model has performed in the free-piston high-enthalpy shock tunnel JAXA-HIEST. To measure heat flux distribution, the eighty-eight and thirty-four fast-response coaxial thermocouples were instrumented on the windward surface and on the back-shell surface, respectively. Besides, Eight Piezo-resistive pressure transducers were mounted on the aft of the body to determine flow establishment around the model through millisecond order short test period. Stagnation enthalpy and stagnation pressure were varied from H_0=3.5MJ/kg to 20MJ/kg, and from P_0=14MPa to 60MPa, respectively. The unit Reynolds number was changed from 0.9 million/m to 4.5 million/m. Aeroheating characteristics was observed at model angle of attack 20 degree with fully laminar, transition and turbulent boundary layer. Turbulent heat flux was observed with 'Pizza-box' shaped isolated roughness elements on the heat-shield surface and back-shell windward surface. Measured heat flux was normalized as Stanton number for comparison with different flow condition.
