Experimental Study of the Mean Flow in a Laminar Axisymmetric Cone Near Wake at Mach Number Equals 6.3 Using Magnetic Model Suspension.
MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB
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Measurements of the Pitot pressure and the recovery temperature of a cylindrical hot-film probe in the laminar near-wake of sharp and spherically-blunted, 7 degree half-angle, adiabatic-wall cones, at M 6.32 and free-stream Reynolds numbers from 88,000in., to 117,000in., are presented. The extent of the region of measurements was from the model based to five base diameters downstream. The cones were supported with a 5-degree-of-freedom magnetic model suspension system. The present study establishes several important effects of hypersonic Mach number on the structure of the axi-symmetric cone near wake when compared with the results of a previous laminar supersonic M 4.3 near-wake investigation of the same model geometry at identical Reynolds numbers. An important finding, among others is a confirmation of the phenomenon of decreasing length of the recirculation region with increasing Mach number. Modified author abstract
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