Accession Number : ADP005131

Title :   Applications of RAE Viscous Flow Methods Near Separation Boundaries for Three-Dimensional Wings in Transonic Flow,

Corporate Author : ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND) AERODYNAMICS DEPT

Personal Author(s) : Firmin,M. C.

Report Date : NOV 1986

Pagination or Media Count : 16

Abstract : Three applications of computational fluid dynamics at high subsonic speeds, with transonic flow, are presented. Two of these relate to the prediction of the pressure distribution over swept wings at conditions close to the separation boundary and one to the design of a swept wing for a wind tunnel model. The methods involved are a potential flow treatment of the inviscid flow coupled with a three dimensional, integral treatment of the turbulent boundary layer. The coupling between the viscous and inviscid flow codes is direct, through a transpiration condition at the wing surface and on a surface downstream of the wing.

Descriptors :   *SWEPT WINGS, *TRANSONIC FLOW, WIND TUNNEL MODELS, BOUNDARY LAYER FLOW, FLOW SEPARATION, PRESSURE DISTRIBUTION, POTENTIAL FLOW, AIRFOILS, INVISCID FLOW, ASPECT RATIO, COMPUTATIONS

Distribution Statement : APPROVED FOR PUBLIC RELEASE