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微型凸起作为减小阻力的一种有效措施已经备受关注。开展了等熵压缩“弱激波”干扰鼓包用于RAE2822超临界翼型的减阻作用机制研究以及NACA0012对称翼型表面脊状结构减阻特性的数值模拟研究。结果表明:通过鼓包参数最优匹配,可达到弱化激波、减小波阻、提高升阻比、延缓抖振边界等目的;同时,通过对比不同脊状结构、不同网格密度对计算结果的影响,总结了多个速度下脊状表面的减阻规律。所得结论为进一步开展微型凸起类流动控制用于机翼的减阻特性研究奠定了坚实基础。
Mini-bumps have drawn much attention as an effective measure to reduce drag. The research on the mechanism of drag reduction using isentropic compression “weak shock ” interference bulge for RAE2822 supercritical airfoil and the numerical simulation research on the drag reduction characteristics of symmetrical airfoil surface ridge structure of NACA0012 were carried out. The results show that: through the optimal matching of bulging parameters, we can achieve the purpose of weakening shock wave, reducing wave resistance, increasing the ratio of lift to drag, and buffering vibration buffering boundary. At the same time, by comparing different ridge structures and different grid densities, Influence, summarizes the drag reduction law of the ridge surface at multiple speeds. The conclusions obtained laid a solid foundation for further research on the drag reduction characteristics of the micro-bump-type flow control wing.