Investigation of the Development of Laminar Boundary-Layer Instabilities Along aCooled-Wall Hollow Cylinder at Mach Number 8

摘要

Measurements of fluctuating flow and mean flow parameters were made in theboundary layer on a cooled wall hollow cylinder model in an investigation of the stability of laminar boundary layers in hypersonic flow. The flow fluctuation measurements were made using constant current hot wire anemometry techniques. Boundary layer profile and model surface conditions were measured to supplement the hot wire data. Testing was done at Mach 8 with free stream unit Reynolds numbers of 1.0 and 1.5 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. Keywords: Hypersonic flow; Wind tunnel flow; Cold wall model; Boundary layer stability; Hot wire anemometry; Hollow cylinder. (JHD)