Generalization of turbojet-engine performance in terms of pumping characteristics /
Newell D. Sanders and Michael Behun.

Description

Main Author

Sanders, Newell D.

Related Names

Behun, Michael.
United States. National Advisory Committee for Aeronautics.

Language(s)

English

Published

Washington, D.C. : National Advisory Committee for Aeronautics, 1949.

Subjects

Airplanes > Airplanes / Motors > Airplanes / Motors / Performance.
Airplanes > Airplanes / Turbojet engines.

Summary

Characteristics of a basic turbojet engine consisting of compressor, combustor, and turbine can be presented in terms of pumping characteristics; that is, corrected air flow, ratio of engine-outlet to -inlet total pressure, ratio of engine-outlet to -inlet total temperature, Reynolds number index, corrected engine speed, and corrected fuel-air ratio. Such a presentation describes the engine independently of the characteristics of other elements of the propulsion system. This method of presentation also permits rapid estimation of performance of complex propulsion systems involving the basic tubojet engine.

Note

NACA TN No. 1927.
"August 1949."

Physical Description

33 p. : ill. ; 28 cm.

Locate a Print Version

Find in a library

Viewability