Three-dimensional boundary layer calculations on wings, starting from the fuselage

A computational method for three dimensional turbulent boundary layers is presented. The turbulence model is a simple eddy viscosity formulation. A hybrid difference scheme which has the robustness of first order schemes and accuracy of second order schemes is used. The boundary layer is computed in the region of determinacy of the initial data. No extra data has to be given along the lateral boundaries of the computational domain. Results of the boundary layer flow over the fuselage of an aircraft-like body are presented. The computation follows the strongly three dimensional flow over the leading edge of the fairing and wing, after the boundary layer on wing upper and lower surface is computed.