In order to obtain a fundamental configuration in the development of aircraft, characteristics of an initial candidate and various alternative configurations are estimated by CFD (Computational Fluid Dynamics) and wind tunnel tests. Performance of them are compared and evaluated, and a final configuration which satisfies the demand of performance is decided. These are the general process of design. However, it requires a great deal of labor to obtain optimal configurations by parametric study, and this process has a tendency to depend on designer's experiences. Recently, application of optimal design to aerodynamic shapes is carried out all over the world so as to solve these problems. Optimal design is making practicable with the advance of CFD and computational speed, and automatic parametric study makes it possible to reduce the required time to design process. There is every possibility that nacelles for a practical SST will be hanged below wings. It is important to reduce interference drag among wings, nacelles and fuselage. The twist angles, the camber and the position of nacelles for main wings are parameters which affect the reduction of interference drag. However in order to simplify the computation process, twist angles are selected as design parameters. In this study, an optimization of twist angles for SST wing-nacelle configuration was carried out so that the drag coefficient was reduced under a constant lift coefficient. For the optimal configuration, the twist of main wings near the position of nacelle installation brought the reduction of the drag coefficient by about five counts.
ナセル付きSST主翼の捻り角最適化
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