Accession Number:

ADA021406

Title:

Measurements of Boundary Layer Transition on a Shock Tube Wall for Wall Cooling Ratios between 0.39 and 0.255.

Descriptive Note:

Final rept.,

Corporate Author:

FRANK J SEILER RESEARCH LAB UNITED STATES AIR FORCE ACADEMY COLO

Personal Author(s):

Report Date:

1975-12-01

Pagination or Media Count:

32.0

Abstract:

Measurements of boundary layer transition on a shock tube wall have been made in the Frank J. Seiler Research Laboratorys 17 inch diameter shock tube for wall cooling ratios between 0.39 and 0.255. The data indicate that a reversal region does not exist in this wall cooling range. The majority of the measurements was made for a unit Reynolds number of 50 thousand per ft. Test times were measured but no acoustic measurements were made. Hot-wire or cold-wire measurements are suggested for future experiments.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE