Accession Number : AD0787883
Title : Experimental Study of the Mean Flow in a Laminar Axisymmetric Cone Near Wake at Mach Number Equals 6.3 Using Magnetic Model Suspension.
Descriptive Note : Final rept.,
Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB
Personal Author(s) : Blankson,Isaiah M.
Report Date : JUN 1973
Pagination or Media Count : 145
Abstract : 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 88,000/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)
Descriptors : *Conical bodies, *Reentry vehicles, *Hypersonic flow, Atmosphere entry, Wake, Flow fields, Free stream, Degrees of freedom, Shock waves
Subject Categories : Guided Missile Traj, Accuracy and Ballistics
Distribution Statement : APPROVED FOR PUBLIC RELEASE