Experimental study on high subsonic turbulent flow incipient separation /
by Juan Ming Wu and Hideki Kuwano.

Description

Main Author

Wu, Jain-Ming

Related Names

Kuwano, Hideki, author.
Redstone Arsenal (Ala.)
United States. Army.
University of Tennessee (System). Space Institute

Language(s)

English

Published

Redstone Arsenal, Alabama ; U.S. Army Missile Command, 1976.

Subjects

Wind tunnels > Wind tunnels / Flow visualization.
Aerodynamics.
Turbulent boundary layer.

Summary

For flow over a two-dimensional ramp compression corner case, an experimental investigation to determine the incipient separation was carried out at Mach numbers between 0.55 and 0.9 and Reynolds numbers (based on undisturbed boundary layer thickness) between 350,000 and 690,000. Detailed surface pressure, pitot traversing and oil flow data were obtained for each ramp angle case. Two-dimensionality of the ramp compression corners was verified by the surface oil flow. A major finding of this study is that the incipient separation ramp angle is relatively independent of Mach number and Reynolds number within the range studied. The incipient separation ramp angle was found to be about 22.5 degrees.

Note

Report prepared by The University of Tennessee Space Institute, Tullahoma, Tennessee.
"June 1976."

Physical Description

57 pages : illustrations ; 28 cm

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