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Home > Reference > Research and information: general > Research methods: general > Preliminary Study of Optimum Ductburning Turbofan Engine Cycle Design Parameters for Supersonic Cruising
Preliminary Study of Optimum Ductburning Turbofan Engine Cycle Design Parameters for Supersonic Cruising

Preliminary Study of Optimum Ductburning Turbofan Engine Cycle Design Parameters for Supersonic Cruising


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About the Book

The effect of turbofan engine overall pressure ratio, fan pressure ratio, and ductburner temperature rise on the engine weight and cruise fuel consumption for a mach 2.4 supersonic transport was investigated. Design point engines, optimized purely for the supersonic cruising portion of the flight where the bulk of the fuel is consumed, are considered. Based on constant thrust requirements at cruise, fuel consumption considerations would favor medium by pass ratio engines (1.5 to 1.8) of overall pressure ratio of about 16. Engine weight considerations favor low bypass ratio (0.6 or less) and low wverall pressure ratio (8). Combination of both effects results in bypass ratios of 0.6 to 0.8 and overall pressure ratio of 12 being the overall optimum. Fishbach, L. H. Glenn Research Center NASA-TM-79047, E-9856


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Product Details
  • ISBN-13: 9781724683182
  • Publisher: Createspace Independent Publishing Platform
  • Publisher Imprint: Createspace Independent Publishing Platform
  • Height: 279 mm
  • No of Pages: 32
  • Spine Width: 2 mm
  • Width: 216 mm
  • ISBN-10: 1724683187
  • Publisher Date: 06 Aug 2018
  • Binding: Paperback
  • Language: English
  • Returnable: N
  • Weight: 100 gr


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