Aerodynamic design of complex configurations with junctions

An efficient aerodynamic design tool has been developed adopting a surface mesh movement method for body-installation junctions and an unstructured adjoint method. A three-dimensional unstructured Euler solver is used for flow analysis. Sensitivity analysis is conducted by a discrete adjoint solver. For the geometric modification around body-installation junctions, surface mesh points on aircraft components are moved directly on the curved body surface without any mapping or regeneration of the surface and volume mesh. The present design approach has been applied to ONERA M5 and DLR-F6 wing-body-nacelle-pylon configurations at transonic flow conditions. For ONERA M5, juncture between main wing and fuselage was redefined with wing geometry modification. For DLR-F6, juncture between wing and pylon was redefined with modification of both wing and pylon geometries. In both design examples, shock wave strength was remarkably reduced by the design process. The successful design results validate effectiveness and efficiency of the present design approach for complex configurations with junction interference effects.