Measurements of Boundary Layer Transition on a Shock Tube Wall for Wall Cooling Ratios between 0.39 and 0.255.
Abstract
Measurements of boundary layer transition on a shock tube wall have been made in the Frank J. Seiler Research Laboratory's 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1975
- Accession Number
- ADA021406
Entities
People
- Robert A. Golobic
Organizations
- United States Air Force Academy