Experimental Study of the Mean Flow in a Laminar Axisymmetric Cone Near Wake at Mach Number Equals 6.3Using Magnetic Model Suspension.

摘要

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, 7degree half-angle,adiabatic-wall cones,at M =6.32and free-stream Reynolds numbers from 88,000/in.,to 117,000/in.,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)