4 research outputs found
Charts of Thermodynamic Properties of Air and Combustion Products from 300 Degrees to 3500 Degrees R
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NACA Research Memorandums
Report presenting a study of the effects of high reactor and cycle temperatures and the effect of thickness of high-temperature fuel element materials on the feasibility of the nuclear-powered direct-air-cycle aircraft for flight at Mach number 1.5 and an altitude of 35,000 feet. Testing occurred over a range of reactor fuel temperatures, turbine-inlet temperatures, and reactor fuel plate thicknesses
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NACA Technical Notes
Report presenting charts that permit the determination of enthalpy change for various processes regarding the thermodynamic data of gas properties. Some examples using the charts to solve problems are provided
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NACA Research Memorandums
From Introduction: "The intermediate subsonic speed range is considered and the liquid-metal turbine-propeller cycle discussed in this report. In this report, compressor pressure ratio, heat-exchanger air-inlet Mach number, and turbine-inlet temperature were optimized for maximum engine net thrust per engine-plus-heat-exchanger weight (minimum airplane gross weight) for a range of heat-exchanger effective wall temperature.