An inverse design method for engine nacelles and wings

The application of an iterative design method allows the aerodynamic design of engine nacelles and wings being part of complex aircraft configurations. The method couples a flow solver for the solution of the Euler/Navier–Stokes equations on unstructured grids with a design algorithm which solves the transonic potential equation for small perturbations via an inverse formulation. The accuracy and robustness of the design method is investigated for redesigns of engine nacelles and wings. Several design cases demonstrate the efficient application of the method for the aerodynamic design of installed engine nacelles and wings under influence of complex aircraft configurations. One application shows that the method also can be used to minimize aerodynamic installation effects resulting from the engine integration process by sole nacelle or wing contour shaping. A general design methodology for engine nacelles is derived which allows to take into account all aerodynamic effects on complex configurations during the design process.