Accession Number : AD0608208

Title :   LAMINAR SEPARATED FLOW WITHIN REJOINING OR REATTACHING BOUNDARY LAYERS,

Corporate Author : PRINCETON UNIV N J GAS DYNAMICS LAB

Personal Author(s) : Cheng,Sin-I

Report Date : JUL 1964

Pagination or Media Count : 44

Abstract : The separated flow next to where the supersonic boundary layers rejoin or reattach was studied with the Navier-Stokes equations a round the stagnation point, enclosed between the boundary layers. For the separated, recirculatory flow to be dynamically possible, it was found that at the rear stagnation point the rejoining wake flow must possess: (i) a parabolic dividing streamline (D.S.L.), (ii) a proper axial pressure gradient, and (iii) an outer inviscid stream parallel to the axis of symmetry of the recirculatory flow. Likewise, at the reattachment point, the recirculatory flow must possess (i) a linear D.S.L., (ii) a positive axial pressure gradient and (iii) a given ratio for the slopes of the inviscid streamline over the reattachment point and of the stagnating D.S.L. A model for the analysis of the recirculatory wake is discussed. In the inviscid limit with no initial boundary layer, the model is similar to Chapman's except for the static pressure at the rejoining point and for the overcompression downstream.

Descriptors :   (*JET MIXING FLOW, STAGNATION POINT), (*LAMINAR FLOW, SEPARATION), (*FLUID MECHANICS, NUMERICAL ANALYSIS), PARTIAL DIFFERENTIAL EQUATIONS, WAKE, BOUNDARY LAYER, SUPERSONIC CHARACTERISTICS, PRESSURE, MODEL THEORY, DIFFERENTIAL GEOMETRY

Distribution Statement : APPROVED FOR PUBLIC RELEASE