Tests of a Fixed-Geometry Inlet-Combustor Configuration for a Hydrocarbon-Fueled, Dual-Mode Scramjet

摘要

A NASA/Rocketdyne cooperative research program is ongoing at the NASA Langley Research Center for the purpose of enhancing the dunderstanding of vehicle-integrated, dualmode scramjet engines for missile application operating from Mach 3 to 8 using endothermic hydrocarbon fuels. A complete, gaseous ethy-lene-fueled subscale scramjet engine model will be free-jet tested in the NASA Langley combustion-Heated Scramjet Test Facility. Prior to the engine free-jet tests, however, tests of an inlet/combustor flow-path model were conducted to study the fixed-geometry inlet-combustor design.