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对二维、三维鼓包进行激波控制减阻,并在大型客机的机翼上进行了对比研究。在研究鼓包减阻的机理时,采用了超临界翼型,鼓包的几何形状及鼓包位置的优化也进行了研究。研究结果表明,鼓包位置、形状及串列式分布对机翼的减阻影响较大。最后把得到的研究结果应用到大型飞机的激波减阻上,结果表明,该方法能较大程度地减小激波阻力,进而提高飞机的升阻比,提高飞机的气动效率。
The two-dimensional, three-dimensional drum shock suppression drag reduction, and in the large passenger aircraft wings were compared. In studying the mechanism of drag reduction, the supercritical airfoil, the geometry of the bulge and the optimization of the bulge position were also studied. The research results show that the location, shape and tandem distribution of bulging have a great influence on drag reduction of wing. Finally, the research results obtained are applied to the drag reduction of large aircraft. The results show that this method can reduce the shock resistance to a large extent, and then improve the drag ratio and improve the aerodynamic efficiency of the aircraft.