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Transition Measurements on a 5 Degree Cone in the T4 Shock Tunnel

By David J. Mee


This report presents results from tests to detect boundary layer transition on a 572 mm long, 5 degree semi-angle cone at Mach numbers of 6.0, 6.6 and 8.8 in the T4 Shock tunnel at The University of Queensland. Results are presented for the cone with both a sharp tip and a blunted tip (nose tip radius of 5.4 mm). Results show that transition Reynolds number increases with the unit Reynolds number of the flow and that bluntness delays transition

Topics: transition, shock tunnel, blunt cone, 290201 Aerodynamics
Year: 2001
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