An inlet design concept to reduce flow distortion at angle of attack /
Carl F. Schueller and Leonard E. Stitt.

Description

Main Author

Schueller, Carl F.

Related Names

Stitt, Leonard E.
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, 1957.

Subjects

Charts, diagrams, etc.
Pressure > Pressure / Measurement.
Air flow.
Air ducts.
Diffusers.
Jet engines > Jet engines / Air intakes.

Summary

Detailed pressure measurements were made of the flow distortion just inside the cowl lip of a fixed-cone planar-cowl inlet, a pivoting-cone planar-cowl inlet and a pivoting-cone swept-cowl inlet operated at angles of attack from 0 to 14 degrees and at a Mach number of 1.91. The overa-all pressure recovery and flow distortion at the exit of the three diffusers were also measured.

Note

NACA Research Memorandum E56K28B.
"February 26, 1957."
Title from cover.

Physical Description

23 p. : ill. ; 27 cm.

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