Applications of RAE Viscous Flow Methods Near Separation Boundaries for Three-Dimensional Wings in Transonic Flow,
ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND) AERODYNAMICS DEPT
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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.