Analysis of time accurate pressure measurements in a ramjet/scramjet inlet configuration

摘要

Mean and time accurate pressures have been measured in an inlet of a unfueled Rockwell/Rocketdyne-developed, dual-mode, ramjet/scramjet configuration developed for Rockwell's Hypersonic Research Vehicle. This configuration was designed for low hypersonic Mach number operation using a hydrocarbon-based fuel. A throttling device, attached downstream of the inlet, was used to simulate the effects of upstream propagation of the pressure increase induced by combustion. The time accurate measurements are presented for inlets operating at maximum permissible back pressure and both during and after inlet unstart.