The Supersonic Combustion Facility
The high pressure air system and the new heater built as part of the hypersonic boundary layer facility will provide a source of clean, high temperature, high pressure air for the combustion facility. By building a new settling chamber, nozzle and working section, we will have the additional capability to perform supersonic combustion experiments in two and three-dimensional turbulent flows at static pressures up to 0.4 atmospheres, static temperatures of 300K, with flow run times up to 30 seconds. We have made considerable progress in the design and construction of this facility, and we anticipate it will be ready for the first experiments in the Spring of 1996.