EFFECTS OF COOLING ON TRANSITION IN THE BOUNDARY LAYER ON A HEMISPHERE IN SIMULATED HYPERSONIC FLOW
MICHIGAN UNIV ANN ARBOR
Pagination or Media Count:
A study was made to investigate the effects of cooling on transition in the boundary layer on the nose of a 9-inch diameter hemisphere in simulated hypersonic flow, with the aim of gaining some knowledge of the circumstances under which boundary-layer cooling may promote a reduction in transition Reynolds number transition reversal. The influences of cooling in increasing the stability to Tollmien-Schlichting type disturbances, in decreasing any stabilizing effects of convex curvature, and in increasing the magnitude of disturbances from fixed roughness elements, are discussed.
- Fluid Mechanics