Investigation of the Development of Laminar Boundary-Layer Instabilities along a Cooled-Wall Cone in Hypersonic Flows

摘要

Measurements of fluctuating flow and mean flow parameters were made in the boundary layer on a cooled wall, sharp 7-deg (half-angle) cone in an investigation of wall temperature effects on the stability of laminar boundary layers in hypersonic flow. The flow fluctuation measurements were made using constant-current hot-wire anemometry techniques. Boundary-layer profiles and cone surface conditions were measured to supplement the hot-wire data. Testing was done at Mach numbers 8 and 6 with a free-stream unit Reynolds number of 1.0-million per foot. The test equipment, test techniques, and the data acquisition and reduction procedures are described. Analysis of the hot wire anemometer data is beyond the scope of this report. Hypersonic flow, Wind tunnel tests, Cold wall model, Boundary layer stability, Hot wire anemometry, Sharp cone. (mjm)