The ramp compression type scramjet combustion test in a high enthalpy flow

摘要

Combustion test results with a model scramjet in a high enthalpy shock tunnel HIEST were reported. The test was conducted to verify performance of NAL-E2R scramjet, which showed net thrust under Mach number 8 condition in the vitiated heating wind tunnel RJTF. In order to compare with RJTF result, test condition was tuned to Mach number 8 condition. Gaseous hydrogen was applied as fuel, which equivalence ratio was changed from 0 to 2. Combustion test with different stagnation enthalpy was also conducted to measure the performance of the E2R scramjet under higher flight Mach number condition. The test result showed that the performance of the E2R scramjet in HIEST was equal to that obtained in RJTF. It was concluded that the E2R scramjet can produce net thrust up to Mach number 8 condition. Additionally, it is revealed that the produced thrust was affected considerably with the test flow stagnation enthalpy.