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Performance of a 28-Inch Ramjet Utilizing Gaseous Hydrogen at a Mach Number of 3.6, Angles of Attack Up to 12 Degrees, and Pressure Altitudes Up to 110,000 Feet
Memorandum presenting an investigation conducted in the 10- by 10-foot supersonic wind tunnel to evaluate the performance of a shrouded injector burner with perforated domes employed in a 28-inch ramjet using gaseous hydrogen as fuel. Steady-state data were obtained at a pressure altitude of 77,000 feet and zero angle of attack. Results of the investigation showed that burning could be initiated under severe distortion conditions and that satisfactory combustor operation was accomplished up to a pressure altitude of 110,000 feet with no adverse effect on combustion efficiency.
Date:
May 19, 1958
Creator:
Musial, Norman T.; Ward, James J. & Wasserbauer, Joseph F.
System:
The UNT Digital Library
Performance of a 28-inch ramjet utilizing gaseous hydrogen at a Mach number of 3.6, angles of attack up to 12 degree, and pressure altitudes up to 110,000 feet
Report presenting an investigation in the 10- by 10-foot supersonic wind tunnel to evaluate the performance of a shrouded injector burner with perforated domes employed in a 28-inch ramjet using gaseous hydrogen as fuel. Steady-state data were obtained at a pressure altitude of 77,000 feet and zero angle of attack. Results indicated that burning could be initiated under severe distortion conditions and that satisfactory combustor operation was accomplished up to a pressure altitude of 110,000 feet with no adverse effect on combustion efficiency.
Date:
May 19, 1958
Creator:
Musial, Norman T.; Ward, James J. & Wasserbauer, Joseph F.
System:
The UNT Digital Library