Accession Number : AD0629094
Title : LAMINAR, TRANSITIONAL AND TURBULENT FLOW WITH ADVERSE PRESSURE GRADIENT ON A CONE-FLARE AT MACH 10.
Descriptive Note : Scientific interim rept.,
Corporate Author : NEW YORK UNIV N Y
Personal Author(s) : Zakkay, Victor ; Bos,Alan ; Jensen,Paul F. ,Jr.
Report Date : DEC 1965
Pagination or Media Count : 70
Abstract : An experimental investigation of the boundary layer on a cone-flare body at Mach 10 is presented. Measurements of pressure, heat transfer and boundary layer thickness are made in regions of zero and adverse pressure gradient. Several noses are fitted to the cone to produce blunted cone-flares, which are used to study separation. The experimental results are compared to some recent analytical investigations. The results showed a small amount of blunting can lower the Reynolds number sufficiently to produce separation. The experiment results also showed that a small amount of crossflow (produced by placing the model at small angles of attack) was capable of eliminating separation.
Descriptors : (*CONICAL BODIES, HYPERSONIC FLOW), (*BOUNDARY LAYER, FLOW SEPARATION), PRESSURE, HEAT, NOSE CONES, LAMINAR FLOW, ANGLE OF ATTACK, TURBULENCE, BLUNT BODIES
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE