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- W2324156851 abstract "The shock control bump of supercritical airfoil is numerically investigated by Computational Fluid Dynamics in present paper. The influence of the geometry parameters of the bump is studied by considering the drag reduction performance and robustness. The results show that, the bump location strongly affects on the drag reduction. The best performance is obtained when locating the bump crest at the shock position of the clean airfoil. Higher bump is worse for the drag reduction, while longer bump has good effect in a bigger height range. The bump can effectively weaken the shock wave, suppress the boundary layer separation, and extend the buffet onset boundary, but its working lift coefficient range is relatively narrow. The robustness is an important requirement of engineering application. The results of robustness analysis shows that, the longer and lower bump is more engineering acceptable than the shorter and higher bump, while it could not only improve lift-drag ratio in larger lift coefficient range insensitive to the changes of shapes and Reynolds number, but also increase the drag divergence Mach number." @default.
- W2324156851 created "2016-06-24" @default.
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- W2324156851 date "2014-02-01" @default.
- W2324156851 modified "2023-10-18" @default.
- W2324156851 title "The drag reduction study of the supercritical airfoil with shock control bump considering the robustness" @default.
- W2324156851 doi "https://doi.org/10.1360/132013-185" @default.
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