摘要
为了在实际旋翼翼型设计中考虑粘性影响,采用N-S方程为主控方程,建立了旋翼翼型流场求解方法。使用以Poisson方程为控制方程的网格生成程序生成围绕旋翼翼型的N-S粘性贴体网格,该网格生成程序能在反设计迭代过程中自动更新过渡翼型的粘性网格。在翼型流场计算及网格生成基础上,采用了MGM方程作为翼型反设计方程,建立了一套能够考虑粘性影响的直升机旋翼翼型的反设计方法。应用该方法,分别对二维NACA系列翼型、OA系列翼型、超临界翼型进行了反设计分析,获得了满足要求的二维旋翼翼型,并与目标值(压力分布、升力系数、阻力系数、力矩系数)吻合良好。
In order to consider the viscous effects during the process of actual rotor airfoil design,the method for solving flowfield around the airfoil was developed by using the N-S equations as the governing equations in this paper.The viscous grids around the airfoil were updated by solving Poisson equations,and the viscous grids around transition airfoil could be automatically updateded in the iteration process of adverse design.Based upon the flowfield solver and the grid generation methodology,using the MGM equation as the airfoil inverse equation,a method considering viscous effects for inverse design on helicopter rotor airfoils was established.The inverse design analysis on two-dimensional NACA series airfoil,OA series airfoil,supercritical wing have been performed respectively by using the present method,and it could been seen that in condition of specifying the target value(the pressure distribution,lift coefficients,drag coefficients,moment coefficients),the designed 2-D rotor airfoils have been obtained,and calculated results agreed well with the target value.
出处
《直升机技术》
2011年第1期19-24,共6页
Helicopter Technique
