Laminar boundary-layer separation on flared bodies at supersonic and hypersonic speeds /
by J. Don Gray.

Description

Main Author

Gray, J. Don

Related Names

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

Language(s)

English

Published

Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1965.

Subjects

Laminar boundary layer.
Space vehicles > Space vehicles / Atmospheric entry.

Summary

Experiments at supersonic speeds and at Mach 8 were conducted to determine the conditions which govern the extent of shock-induced laminar flow separations on axisymmetric configurations at zero yaw and without heat transfer. From an extensive correlation of surface pressure data and schlieren photographs, it is shown that the extent of reverse flow is essentially a function of the ratio of the wetted length to the flare divided by the laminar boundary thickness there. As a result, the relative extent of laminar flow separation decreases with a unit Reynolds number increase and grows through an increase in Mach number. Finally, increasing the flare angle increases the length of the reverse flow region.

Note

"January 1965."

Physical Description

58 pages : illustrations, 28 cm

Locate a Print Version

Find in a library

Viewability