Accession Number:

AD0609841

Title:

LAMINAR BOUNDARY-LAYER SEPARATION ON FLARED BODIES AT SUPERSONIC AND HYPERSONIC SPEEDS

Descriptive Note:

Technical Documentary rept.

Corporate Author:

ARO INC ARNOLD AFS TN

Personal Author(s):

Report Date:

1965-01-01

Pagination or Media Count:

59.0

Abstract:

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.

Subject Categories:

  • Aerodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE