15 research outputs found
Effect of heat and power extraction on turbojet-engine performance IV : analytical determination of effects of hot-gas bleed
Effect of heat and power extraction on turbojet-engine performance II : effect of compressor-outlet air bleed for specific modes of engine operation
Loitering and range performance of turbojet-powered aircraft determined by off-design engine cycle analysis
The loitering and range performance of airplanes equipped with several different turbojet engines was analytically investigated by applying the results of off-design cycle analyses to specific airplane characteristics. The method of off-design cycle analysis is presented herein and is verified by a check with experimental data. For all engines considered, the loitering and the range fuel flows obtained with rated tail-pipe nozzle area, variable engine speed operations were within 2 or 3 percent of the optimum fuel flow obtainable with any method of engines operation. The optimum loitering altitude generally occurred between approximately 25,000 and 35,000 feet with corresponding optimum flight Mach numbers of 0.4 to 0.65. In general, the optimum range fuel flows occurred at 3000 to 5000 feet higher altitude and at approximately 0.15 higher flight Mach numbers than the optimum loitering fuel flow
Icing Protection for a Turbojet Transport Airplane : Heating Requirements Methods of Protection, and Performance Penalties
Effect of heat and power extraction on turbojet-engine performance I : analytical method of performance evaluation with compressor-outlet air bleed
Effect of heat and power extraction on turbojet-engine performance III : analytical determination of effects of shaft-power extraction
Analysis of the turbojet engine for propulsion of supersonic fighter airplanes / David S. Gabriel, Richard P. Krebs, E.Clinton Wilcox, Stanley L.Koutz
An analytical investigation was made of two supersonic interceptor type airplanes to determine the most desirable turbojet engine characteristics for this application The airplanes were designed differently primarily because of the amount of subsonic flight incorporated in the flight plan--one flight having none and the other, a cruise radius of 400 nautical miles. Several power plant design variables were varied independently to determine the effect of changes in each parameter on airplane performance. These parameters included compressor pressure ratio, compressor efficiency, turbine-inlet temperature, afterburner temperature, engine specific weight, and air-handling capacity. The effects of using a convergent-divergent exhaust nozzle and of changing the design flight Mach number were also investigated
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NACA Technical Notes
Report presenting the calculation of the effect of air bleed from the compressor outlet on the performance of turbojet engines with variable-area and rated-area tail-pipe nozzles using generalized performance charts. The effect of altitude, compressor-inlet temperature, and flight Mach number on engine performance with air bleed are provided
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NACA Research Memorandums
From Summary: "The loitering and range performance of airplanes equipped with several different turbojet engines was analytically investigated by applying the results of off-design cycle analyses to specific airplane characteristics. The method of off-design cycle analysis is presented herein and is verified by a check with experimental data. For all engines considered, the loitering and the range fuel flows obtained with rated tail-pipe nozzle area, variable engine speed operations were within 2 or 3 percent of the optimum fuel flow obtainable with any method of engines operation. The optimum loitering altitude generally occurred between approximately 25,000 and 35,000 feet with corresponding optimum flight Mach numbers of 0.4 to 0.65. In general, the optimum range fuel flows occurred at 3000 to 5000 feet higher altitude and at approximately 0.15 higher flight Mach numbers than the optimum loitering fuel flow.
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NACA Technical Notes
Report analyzing and discussing the problems associated with providing icing protection for the critical components of a typical turbojet transport airplane operating over a range of probable icing conditions. Heating requirements for several thermal methods of protection are evaluated and the airplane performance penalties associated with providing protection from various energy sources are provided