被动孔隙控制的数值模拟研究

被动孔隙控制是一种在飞行器表面压力分布差别较大的若干区域开孔,将其下的通风腔连通进行表面压力自由调节,从而实现气动噪声、激波诱导附面层分离甚至气动力与力矩控制的技术。孔隙控制的数值模拟可对每个开孔都生成网格,但计算量非常大。为节约计算开销,可根据孔洞流动细节,建立孔隙边界模型,推导孔隙边界条件。本文在自主研发的RANS方程数值模拟框架下,结合该边界条件完成了孔隙外流场的数值模拟。模拟结果与文献实验数据相当吻合,证明孔隙边界条件完全可用于被动孔隙控制的数值模拟研究,同时也显示被动孔隙控制是一种大有潜力的气动控制手段。

Numerical simulation of flow over porous surfaces

The passive porosity control concept is a promising technique for maneuver control of tailless aircraft at a low speed,high angle of attack condition,and has been investigated by NASA with wind tunnel experiments and numerical simulations.In present paper,the porous surface boundary condition developed by N.Frink et al is implemented in our RANS solver to simulate flow over porous surfaces on a tangent-ogive cylinder and a GA(W)-1 wing.Results indicate that simulation based on this boundary condition can obtain the aggregate aerodynamic effects agreed well with NASA's experimental data.This modeling approach is feasible for research on the passive porosity control.