For wing design purposes the value of maximum lift angle is an important quantity. At the high Reynolds Numbers in naval architecture flows the onset and development of turbulent separation is the deciding value for the maximum lift angle. For the calculation of separated turbulent flows usually fully viscous flow solvers, like e.g. Reynolds averaged Navier Stokes (RANS) Solvers, are used. Instead of this kind of solvers, which are expensive by means of computational time, also interacting boundary layer (IBL) methods can be used. Due to the viscous-inviscid coupling, these methods are able to compute flows with limited separation up to the maximum lift angle and represent a cheap and robust alternative to higher value viscous solvers. In this paper a turbulent boundary layer method solving the integral momentum equation together with the integral energy equation of the boundary layer in an inverse formulation is described. The method is combined with an existing inviscid flow solver for 2D wing section flows and a laminar boundary layer method code including transition forecast.

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