Effects of acoustic and vortical disturbances on the turbulent boundary layer at free-stream Mach number 0.5 /
John A. Benek.

Description

Main Author

Benek, John A.

Related Names

United States. Air Force.
Arnold Engineering Development Center
ARO, Inc.

Language(s)

English

Published

Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1977.

Subjects

Whirlwinds.
Sound-waves.
Turbulent boundary layer.

Summary

An experimental investigation of the effects of free-stream disturbances on the development of a turbulent boundary layer is described. The data, obtained at a free-stream Mach number of 0.5, indicated: (1) compared to the baseline acoustic disturbances of 133 db, acoustic disturbances of up to 150 db did not significantly alter the turbulent boundary-layer skin friction, displacement thickness, or momentum thickness and (2) compared to the baseline vortical disturbances of 0.5 percent of the free-stream velocity, vortical disturbances of one percent of the free-stream velocity considerably altered the boundary-layer skin friction, displacement thickness, and momentum thickness, as well as their growth rates. (Author).

Note

"December 1977."
"Final Report: July 1, 1974 -- June 30, 1976."

Physical Description

99 pages : illustrations ; 28 cm

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