Initial Conditions for the Prediction of Boundary Layers on Wings and Fuselages

Abstract

It is well-known that boundary-layer theory cannot be applied to the prediction of the complete flow field past an aircraft configuration, because the boundary-layer approach is not valid, for instance, for the flow along wing-fuselage junctions and along wing tips (see Fig. 6.1). The boundary-layer on portions of the aircraft, such as on wings or fuselages, can, however, be predicted quite well as long as the flow remains attached to the body surface.