
Accession Number : AD0481918
Title : THE PRESSURE FIELD IN COMPRESSIBLE BOUNDARY LAYER THEORY  A CRITICAL REEXAMINATION AND TREATMENT,
Corporate Author : GENERAL ELECTRIC CO PHILADELPHIA PA MISSILE AND SPACE DIV
Personal Author(s) : Weinbaum, Sheldon ; Garvine, Richard W.
Report Date : MAR 1966
Pagination or Media Count : 36
Abstract : The behavior and effect of pressure waves in a supersonic boundary layer are examined, and the assumptions of compressible and higher order boundary layer theory are critically reassessed. Qualitative arguments are presented which indicate that some of the matching techniques and concepts of compressible boundary layer theory which have been borrowed directly from the incompressible theory may not always be valid. Generally, a transition region will exist between the inner viscous and outer inviscid flows wherein the streamwise pressure gradient varies significantly through the boundary layer, and inviscid pressure mechanisms may significantly affect the growth of the normal velocity. A new method is outlined treating viscousinviscid flows with arbitrary pressure field where the viscous regions exhibit a boundary layer behavior. The aim is to develop a solution uniformly valid for the disturbed region. The method employs a combined numerical characteristics implicit difference scheme for solving the system of hyperbolicparabolic differential equations that govern the flow. (Author)
Descriptors : *COMPRESSIBLE FLOW), (*BOUNDARY LAYER, (*SUPERSONIC FLOW, BOUNDARY LAYER), PRESSURE, FLOW FIELDS, THEORY, VELOCITY, NUMERICAL METHODS AND PROCEDURES, PARTIAL DIFFERENTIAL EQUATIONS, HYPERSONIC FLOW, SLENDER BODIES, FLOW SEPARATION, WAKE, TEMPERATURE, NUMERICAL ANALYSIS, LAMINAR FLOW, SHOCK WAVES, MATHEMATICAL MODELS, REYNOLDS NUMBER, VISCOSITY.
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE