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描述了增升装置在提高舰载机薄翼型升力系数方面的作用,观察到大偏角前缘襟翼小迎角时对翼型升力曲线的影响,并通过与试验现象对比,初步探讨了非线性作用形成的可能机理。利用数值模拟方法,通过有限元计算软件对相同流场中多种增升装置的升力系数进行了模拟与比较,从而达到合理设计舰载战机翼型的目的。CFD计算结果表明,所设计的二维多段翼型有良好的气动特性,升力系数得到提高,具有较好的增升效果。
Describes the role of the lifting device in improving the lift coefficient of the thin airfoil of the carrier-based aircraft. The influence of the large angle leading edge flap on the lift curve of the airfoil at a small angle of attack is observed. By comparing with the experimental phenomenon, The possible mechanism for the formation of nonlinear effects. The numerical simulation method is used to simulate and compare the lift coefficient of many kinds of lifting devices in the same flow field by finite element software so as to achieve the purpose of designing the ship airfoil warfighting airfoil rationally. The results of CFD show that the designed two-dimensional multi-section airfoil has good aerodynamic characteristics, lift coefficient is improved, and has a good effect of increasing.