The facility was designed in support of the Air Force Hypersonic Technologies (HyTech) program for long-duration, steady-state combustor tests. Research conducted in this facility is in pursuit of technological breakthroughs in ignition, fuel injection, and flameholding for supersonic combustion, and will provide local experience in the areas of high-speed propulsion systems testing and analysis. Facility calibration is complete, and recent experiments and computations have investigated ignition and combustion of liquid and gaseous hydrocarbon fuels in supersonic flow. Combustion inlet conditions simulated Mach numbers of 4-6 and dynamic pressure of 1000 psf. Temperature, thrust, and pressure measurements were made, and visual video records indicate an active combustion zone with rapid flame spreading. An aerated-fuel injection experiment has been conducted as an extension of a separate experimental program researching the fundamental spray structure of aerated-liquid jets in a supersonic crossflow environment.