Solution of an Inverse Problem for a 2-D Turbulent Flow Around an Airfoil

The presented method is intended for a solution of an airfoil design inverse problem. It is capable of suggesting an airfoil shape corresponding to a given pressure distribution on its surface. The method is an extension of a method presented earlier. Using the k - omega turbulence model it can handle a turbulent boundary layer which improves its applicability. The method is aimed to a subsonic flow, the angle of attack is one of the results of the method. The method is based on the use of an approximate inverse operator coupled with the Navier Stokes equations equipped with the turbulence model. The equations describing the flow are solved using an implicit finite volume method, the linearized system is solved by the GMRES method. Numerical results are also presented.