Book Description
This was an experimental and analytical investigation to supply design information for the aerothermo design of a supersonic combustor for a flight test vehicle. The penetration of fuel jets into a supersonic stream was investigated in a cold flow supersonic wind tunnel and combustion test of scale model combustors were conducted in a Hypersonic Arc-Tunnel. Combustion tests of several configurations identified a burner having adequate performance characteristics for achieving the vehicle mission. The aerothermo design of the vehicle combustor was based on this tested configuration. This volume is devoted to investigations of Fuel Injection and Combustion in supersonic airstreams. (Author).