RESULTS OF RAMJET FACILITY MODEL TESTS AT MACH 7

Abstract : A test program was conducted to provide ramjet test facility bypass flow second throat diffusers pressure recovery data at a nominal nozzle exit Mach number of 11.0. During the tests, studies were made to determine the effects of Reynolds number, diffuser throat length, inlet capture, area, and other variables. The pressure recoveries obtained during the testing proved to be somewhat better than the original expectations. The peak junning pressure recovery was over 60% of free stream normal shock recovery with the adjustable diffuser. Starting pressure recoveries were somewhat lower and ranged mostly from 20% to 30% of normal shock.