USE OF THE RATIO OF SPECIFIC HEATS IN THE DETERMINATION OF TURBOJET ENGINE THRUST.

Abstract

The memorandum presents general equations for the calculation of the idealized thrust and thrust correction factor for determination of turbojet engine thrust. Tables of specific heat ratios versus exhaust gas temperature are given. An analysis shows the difference between the use of a constant gamma and a variable gamma. Finally, an explanation of specific heat ratios and a method of choosing an applicable ratio are discussed. Consideration should be given the selection of gamma when the thrust equations are applied. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jul 02, 1968
Accession Number
AD0671898

Entities

People

  • William R. Simpson

Organizations

  • Naval Air Station Patuxent River

Tags

DTIC Thesaurus Topics

  • Combustion Products
  • Engines
  • Equations
  • Exhaust Gases
  • Fluids
  • Gases
  • Jet Aircraft
  • Jet Engine Exhaust
  • Specific Heat
  • Turbojet Engines

Fields of Study

  • Physics

Readers

  • Internal Combustion Engine (ICE) Technology.
  • Regression Analysis.