Aerodynamic optimization of high-wing configuration for near future aircraft

This paper presents the aerodynamic optimization of high-wing configuration. The present optimization aims to explore the fuselage-wing shape suitable for high-wing configuration as near-future aircraft, which is capable to install higher bypass ratio engines, using computational fluid dynamics simulation and the Kriging-surrogate-assisted genetic algorithm. First, we optimize the fuselage upper surface including fairing for the high-wing configuration and investigate the interference effect between the fuselage upper surface and the wing. Second, the aircraft nose shape is also optimized together with the fuselage upper surface to achieve higher lift generated by the fuselage itself. Finally, both the fuselage shape and the wing shape are optimized to improve lift-to-drag ratio (L/D) by alleviating shock wave without spoiling the lift generation mechanisms established in the first and the second optimizations. The final optimized configuration reduces shock wave and achieves much higher lift coefficient of 0.742, which is generated by not only the wing but also the fuselage, than the low-wing DLR-F6 configuration.