Multi-point design of wing-body-nacelle-pylon configuration

Aerodynamic design optimization is conducted for DLR-F6 wing-body-nacelle-pylon configuration adopting an efficient surface mesh movement method. A three-dimensional unstructured Euler solver and its discrete adjoint code are utilized for flow and sensitivity analysis, respectively. Two design conditions considered are a low-lift condition and a cruise condition in transonic regime. Design objective is to minimize drag and reduce shock strength at both flow conditions. Shape deformation is made by variation of the section shapes of inboard wing and pylon, nacelle vertical location and nacelle pitch angle. Hicks-Henne shape functions are employed for deformation of the section shapes of wing and pylon. Design iterations converged to obtain drag coefficients remarkably reduced at both design conditions retaining specified lift coefficient and satisfying constraints. Two-point design results show mixed features of the one-point design results at low-lift condition and cruise conditions.