Investigation at supersonic speeds of the compressor stall and inlet buzz characteristics of a J34 - spike-inlet combination /
J. Cary Nettles and Robert C. Campbell.

Description

Main Author

Nettles, J. Cary.

Related Names

Campbell, Robert C.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics.
United States. National Advisory Committee for Aeronautics.

Language(s)

English

Published

Washington, D.C. : National Advisory Committee for Aeronautics, 1958.

Subjects

Charts, diagrams, etc.
Compressors.
Aerodynamics, Supersonic.
Vibration (Aeronautics)
Jet engines > Jet engines / Air intakes.
Airplanes > Airplanes / Turbojet engines.

Summary

For a Mach number range from 1.6 to 2.0 and angles of attack from 0 to 9 degrees the occurrence of stall was related to the presence of a pressure deficiency at the hub of the compressor. The referred engine air flow tended to increase as radial distortion level increased. Approaching the inlet buzz limit with the engine operating in or near a stall condition did not affect the minimum stable air flow of the diffuser, and conversely the presence of mild buzz did not affect the compressor stall limit. The stability limits of a 15 degree plus 10 degree double-cone inlet were essentially the same with the engine as with a choked plug.

Note

NACA Research Memorandum E57K19B.
"March 5, 1958."
Title from cover.

Physical Description

30 p. : ill. ; 27 cm.

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