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对30P30N三段翼型失速攻角附近的分离流动进行了数值模拟研究。为了抑制大攻角时背风区的流动分离,在主翼段上表面引入了行波壁变形模型和抛物型局部主动振动模型,利用作者以往发展的动态混合网格技术和相应的非定常计算方法,对变形过程中的非定常分离流动进行了数值模拟,分析了各种变形参数对流动分离的影响。计算结果表明,在适当的条件下,局部主动变形能够抑制翼型背风区的分离,由此可以起到增升减阻的作用,改善翼型的气动性能。
The numerical simulation of the separation flow around the angle of attack of the 30P30N three-stage airfoil is carried out. In order to restrain the flow separation of the leeward area at high angle of attack, a traveling wave wall deformation model and a parabolic local active vibration model are introduced on the upper surface of the main wing section. Based on the dynamic hybrid grid technology and corresponding unsteady calculation methods developed by the author, The unsteady flow in the deformation process is numerically simulated and the influence of various deformation parameters on the flow separation is analyzed. The calculation results show that under proper conditions, the local active deformation can restrain the separation of the airfoil leeward zone, which can enhance the drag reduction and improve the aerodynamic performance of the airfoil.