USE OF THE RATIO OF SPECIFIC HEATS IN THE DETERMINATION OF TURBOJET ENGINE THRUST.
NAVAL AIR TEST CENTER PATUXENT RIVER MD
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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
- Jet and Gas Turbine Engines