A THEORETICAL PERFORMANCE INVESTIGATION OF AN AFTERBURNING TURBOFAN ENGINE

Abstract

This study presents results of a theoretical evaluation of the performance of an afterburning turbofan engine when used for high altitude, high speed flight. The calculated performance is compared with that of a conventional turbojet, and also a combination ramturbojet, by means of the performance parameters of specific fuel consumption and specific thrust. As the study involved a considerable amount of calculations, the problem was coded in Fortran computer language by the writer. The results of the study were generated by the Control Data Corporation model 1604 digital computer of the Postgraduate School. The results of the study indicate that above Mach 2 the afterburning turbofan shows an increasing performance advantage with increasing Mach number and altitude over the turbojet engine.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1962
Accession Number
AD0479693

Entities

People

  • James F. Bell

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aircraft Industry
  • Aircrafts
  • Altitude
  • Combustion
  • Computer Programs
  • Computers
  • Exhaust Gases
  • Fuel Consumption
  • Gas Turbines
  • High Altitude
  • Jet Aircraft
  • Jet Engines
  • Mach Number
  • Specific Heat
  • Turbines
  • Turbofan Engines
  • Turbojet Engines

Readers

  • Aerospace Engineering
  • Computer Science.