Measurements of Boundary Layer Transition on a Shock Tube Wall for Wall Cooling Ratios between 0.39 and 0.255.
FRANK J SEILER RESEARCH LAB UNITED STATES AIR FORCE ACADEMY COLO
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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.
- Fluid Mechanics