Accession Number : AD0755862
Title : Viscous Flow Over a Cone at Moderate Incidence. II. Supersonic Boundary Layer,
Corporate Author : POLYTECHNIC INST OF BROOKLYN FARMINGDALE N Y DEPT OF AEROSPACE ENGINEERING AND APPLIED MECHANICS
Personal Author(s) : Lin,T. C. ; Rubin,S. G.
Report Date : SEP 1972
Pagination or Media Count : 102
Abstract : A numerical finite difference method recently developed to study three-dimensional viscous flow is applied here to the supersonic flow over a sharp cone at moderate angles of incidence (a/0 < 2, a=angle of attack, 0=cone half angle). In a previous analysis, the hypersonic merged and strong interaction regions were considered. In this paper the supersonic boundary layer farther downstream is evaluated. The system of governing equations incorporates lateral diffusion and centrifugal force effects; and an improved numerical scheme has been developed. Detailed flow structure including surface heart transfer, boundary layer profiles and thickness, and the formation of swirling pairwise symmetric vortices, associated with crossflow separation are obtained.
Descriptors : (*CONICAL BODIES, *SUPERSONIC CHARACTERISTICS), THREE DIMENSIONAL FLOW, ANGLE OF ATTACK, INTERACTIONS, VISCOSITY, SURFACE TEMPERATURE, EQUATIONS OF MOTION, FLOW SEPARATION, VORTICES, EXPERIMENTAL DATA, HEAT TRANSFER, MATHEMATICAL MODELS
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE