An investigation of several NACA 1-series nose inlets with and without protruding central bodies at high-subsonic Mach numbers and at a Mach number of 1.2 /
Robert E. Pendley and Harold L. Robinson.

Description

Main Author

Pendley, Robert E.

Related Names

Robinson, Harold L.
Langley Aeronautical 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, 1950.

Subjects

Charts, diagrams, etc.
Wind tunnel testing.
Aerodynamic load.
Jet engines > Jet engines / Air intakes.
Air ducts.
Noses (Aircraft)

Summary

An investigation of three NACA 1-series nose inlets, two of which were fitted with protruded central bodies, was conducted in the Langley 8-foot high-speed tunnel. An elliptical-nose body, which had a critical Mach number approximately equal to that of one of the nose inlets, was also tested. Tests were made near zero angle of attack for a Mach number range from 0.4 to 0.925 and for the supersonic Mach number of 1.2. The inlet-velocity-ratio range extended from zero to a maximum value of 1.34. Measurements included pressure distribution, external drag, and total-pressure loss of the internal flow near the inlet. Drag was not measured for the tests at the supersonic Mach number.

Note

NACA Research Memorandum L9L23A.
"February 21, 1950."
Title from cover.

Physical Description

53 p. : ill. ; 27 cm.

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