Memorandum presenting an analysis to determine the compressor pressure ratios and specific weight flows obtainable with single-stage air-cooled turbines for both nonafterburning and afterburning turbojet engines operating at a flight Mach number of 2 in the stratosphere. Wide ranges in turbine-inlet temperature, tip speed, hub-tip radius ratio, and coolant-flow ratio were considered.

Report presenting an investigation of a conservatively designed experimental cold-air turbine with and without a shroud band on the rotor blades. The tip of the rotor blade was oriented toward the tangential direction so that the adverse effect of blade-tip scraping would not be appreciable. The efficiency for the unshrouded-rotor configuration was about one point higher than for the shrouded rotor.

Report presenting an investigation to study the aerodynamic problems associated with a turbine design for a mode of engine operation which utilizes turbine stator adjustment to maintain a fixed compressor operating point. An indication of the turbine requirements for a particular compressor operating point indicated that a feasible sing-stage air-cooled turbine design could be obtained within reasonable aerodynamic limits. Results regarding the performance of the turbine, pressure ratios, and operational requirements are provided.

Report presenting an investigation of combustion oscillations using white fuming nitric acid and a hydrocarbon fuel in a 1000-pound-thrust rocket engine. Results regarding rotary oscillation shown by 40,000-frame-per-second photographs, oscillations recorded by streak photography, ion gap traces, pressure measurements, and plastic chamber erosion are provided.

Economic study covering several classes of cycles of reactor steam power plants.