Investigation of a simple device for preventing separation due to shock and boundary-layer interaction /
Coleman duP. Donaldson.

Description

Main Author

Donaldson, Coleman duP.

Related Names

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.
Turbulence.
Shock waves.
Vortex generators.
Boundary layer.
Aerofoils.

Summary

Results are presented of a preliminary investigation of vortex generators introduced into the region of boundary layer to increase the turbulent mixing, in an attempt to prevent separation due to boundary-layer and shock interaction. Prevention of such separation and some of its adverse effects up to Mach numbers ahead of the shock of the order of 1.4 appears possible by means of this simple device. Preliminary flight tests show that this method is effective in controlling shock-induced separation on the wing of an airplane at high speed.

Note

NACA Research Memorandum L50B02A.
"November 29, 1950."
Title from cover.

Physical Description

34 p. : ill. ; 27 cm.

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