Approach and facility for aerodynamic thermal test by lower speed and high-temperature gas flow

Comparability of flow parameters and surface heal flux density on a typical leading structure by these two heating approach was analyzed, it was demonstrated to be feasible of utilizing lower-speed and high-temperature gas flow as heating method for hypersonic aerodynamic thermal test. A new combined heating scheme composed of a lower-speed and high-temperature gas flow and quartz lights was proposed for hypersonic aerodynamic test of blunt cone's. The newly-built aerodynamic thermal tester was designed with an efficient double-chamber vaporizing combustor, a new water-cooled pipe structure with thermal insulation sandwich of keramic material bearable high temperature, electric pre-heaters and twin-fule-supply scheme for the combustor. It can generate a hot gas of 2100 K. The average gradient of radial temperature distribution of φ250 mm nozzle is about 3 K/mm. And the tester has auto-linear-control ability of temperature and the temperature difference is 46 K. In a word, it can meet the urgent requirement for thermal test of high temperature and high heat flux of hypersonic vehicle flying by 24 km height and mach number 6 speed.