An experimental investigation of shock wave -- boundary layer interaction dynamics /
G.W. Braun, W.T. Snyder.

Description

Main Author

Braun, Gerald W.

Related Names

Snyder, William T., author.
Air Force Flight Dynamics Laboratory (U.S.)
University of Tennessee (System). Space Institute

Language(s)

English

Published

Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1969.

Subjects

Airplanes > Airplanes / Motors.
Boundary layer control.
Shock waves.

Summary

Wind tunnel tests were performed which simulated the flow pulsations which are sometimes produced in engine inlets by shock-boundary layer interaction. Shock Mach numbers from 1.2 to 1.4 were used and the boundary layer was influenced by air bleeding in or sucking off. The flow was observed by shodowgraph and static and total pressures were measured by means of low frequency and high frequency response instruments. Static wall pressures, boundary layer pressure profiles, and total pressure distributions across several tunnel cross sections were plotted. The data were analyzed with respect to their rms value and power spectral density. A literature survey and an analytical investigation of the pulsations in a diffuser with nonviscous flow are included. (Author).

Note

"October 1969."

Physical Description

xii, 105 pages : illustrations ; 28 cm.

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