Abstract
Aerodynamic heating test has performed in the free-piston high-enthalpy shock tunnel JAXA-HIEST. A HRV 6% scale model has applied in the test, which model dimension was decided as a reference configuration of HRV. The model has eighty-eight fast-response coaxial thermocouples on the windward surface to measure heat flux distribution. Thirty-four thermocouples and eight Piezo-resistive pressure transducers were also instrumented on the aft of the model and were used to determine flow establishment around the model through test period. Stagnation enthalpy and stagnation pressure were varied from H_0=3MJ/kg to 25MJ/kg, and from P_0=14MPa to 52MPa, respectively. The unit Reynolds number was changed from 0.9 million/m to 4.5 million/m. Aeroheating characteristics were observed at model angle of attack 0 degree and 20 degree with fully laminar or with transitional boundary layer. Measured heat flux was normalized by the products of the Stanton number and the square-root of the Reynolds number for comparison with other wind tunnel test results. In the present test campaign abnormally high heat-flux phenomenon was observed, which phenomenon appeared under stagnation enthalpy H_0 > 13MJ/kg and stagnation pressure P_0 > 45MPa
