基于分区拼接网格技术高升力装置流场数值模拟

针对高升力装置构型模型结构复杂、流场变化剧烈等特点,本文采用分区拼接网格的思想分别按照流场和结构拓扑特点对高升力装置进行了网格分区。在分区的基础上逐块生成网格,减小了增升装置网格的生成难度,提高了网格质量,减少了网格数目。首先,研究了高升力装置的分区策略及流场特点;接着以MD30P-30N多段翼型为研究算例研究了网格比例和插值方法对计算结果的影响。经过分析对比可知:外部区域与近壁区域之间的比例不宜小于1:5;内部域网格比例不宜超过1:1.8,最好保持在1:1左右;计算中应该采用高阶精度插值以保证计算精度。采用某四段翼型进行了验证;最后采用NASA标准高升力装置进行了三维高升力装置流场数值模拟并与相应风洞实验数据及对接网格计算结果进行了比较与分析,验证了拼接网格技术的高效性与可靠性。同时分析研究了绕三维增升装置的流动及其周围复杂的粘性流动现象。

Numerical simulation of flow around high-lift device based on zonal patched-grid technology

Due to the complexity of the configuration and flow field of high-lift devices,the flow filed is divided into small domains based on the topology of the configuration and the characteristics of the flow.The mesh is set up part by part based on zone,and the difficulty of the generation of grid is decreased,the number is also decreased.The strategy of dividing and characteristic of flow field around the high-lift device is studied firstly.Then by choosing the MD 30P-30N multi-element airfoils as the computational model,the proportion of the mesh and the interposition method which will affect the precision and stability is studied.The scale between outer area and near wall zone should less than 1:5;the scale of the near wall zone should less than 1:1.8;the high accurate interpolation method should be used.A multi-element airfoil is chosen to test the method.Finally,the flow around NASA high-lift model is simulated based on patched-grid technology.The results are compared with wind tunnel experimental data and the results computed by 1 to 1 multi-block structural grid.It is proved that patched-grid technology is reliable and efficient.At the same time,the viscous flow around the high-lift device is also studied.