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系统研究机翼结冰计算中水滴轨迹和撞击特性的计算方法,将网格扇形分区和单元拓扑结构思想应用于水滴轨迹计算,引入欧拉法、预估-校正、四步Runge-Kutta法离散求解水滴运动方程.基于三维NACA 0012机翼模型,讨论水滴所在位置判断、速度插值和表面收集系数的计算方法,分析方程离散格式、水滴释放位置对计算结果的影响.采用三维机翼计算收集系数分布,并与试验结果进行对比,分析水滴直径对收集系数的影响;最后,将水滴计算模块DROP3D集成于结冰软件计算平台,计算不同工况参数下,机翼表面的气流流场和水滴撞击特性及结冰冰形,进一步验证程序的运行性能.
The calculation method of water drop trajectory and impact characteristic in wing icing calculation is systematically studied. The idea of grid sector-shaped partition and element topology is applied to the calculation of water droplet trajectory. Euler method, predictor-corrector, Runge-Kutta method The equations of water drop motion are solved.The three-dimensional NACA 0012 airfoil model is used to discuss the calculation method of water drop position judgment, velocity interpolation and surface collection coefficient, and to analyze the influence of discrete equation and water droplet release position on the calculation results. And then compared with the experimental results to analyze the influence of the droplet diameter on the collection coefficient. Finally, the DROP3D module was integrated into the icing software platform to calculate the flow field and droplet impact on the wing surface under different operating parameters Features and icing ice shape, to further verify the operation of the program performance.