The variation or combustion efficiency with fuel/air ratio and pressure altitude and the effects of combustion-chamber-inlet velocity and altitude on the operating range of fuel/air ratio are presented from actual flight tests or a 20-inch-diameter steady-flow ramjet engine. Starting characteristics and general performance are also discussed. For the entire range of pressure altitudes from 5000 to 30,000 ft and for free-stream Mach numbers up to 0.51, the ramjet operated smoothly with the exception of occasional rough operation at excessively rich mixtures.
Flight Investigation of a 20-Inch-Diameter Steady-Flow Ram Jet
1948
33 pages
Report
Keine Angabe
Englisch