OA212翼型主动流动控制的数值模拟研究

采用数值模拟的方法,探讨了基于零质量射流的主动流动控制技术对OA212旋翼翼型动态失速的控制效果和控制特性.以积分形式雷诺平均Navier-Stokes(N-S)方程为控制方程,采用格心有限体积法进行求解.空间离散采用AUSM~+-up格式,时间推进采用含牛顿型LU-SGS子迭代的全隐式双时间法,且引入了预处理方法和多重网格方法加速收敛.通过在喷口上施加非定常边界条件来模拟射流对翼型绕流的影响.研究了不同类型射流、不同位置射流以及不同控制参数(频率、相位、偏角、动量系数等)对动态失速控制效果的影响.研究表明:零质量射流和传统的定常射流均可减小动态失速迟滞环的回线面积,但在提高最大升力方面零质量射流明显优于定常射流;在12%c和62%c处施加组合零质量射流的控制效果最为明显.

Numerical simulation of active dynamic stall control on an OA212 rotor airfoil

In this paper, the active dynamic stall control using synthetic jet on an oscillating OA212 airfoil at high angle of attack is simulated and discussed. Cell-centered finite-volume scheme is used to discrete the unsteady Reynolds-Averaged Navier-Stokes equations of integral form. An AUSM~+-up upwind scheme and a fully implicit dual-time step method are utilized for spatial discretization and time stepping, respectively. Implicit preconditioning method and geometric multigrid method are also both employed to remove the stiffness encountered in simulation of low-speed flows and accelerate the convergence of computation. The influence of synthetic jet on the main flow is modeled by a generalized unsteady blowing/suction boundary condition. Different types of jets at different locations are simulated, and the influence of frequency, phase shift, jet angle and momentum coefficient on the outcome of control are studied. It indicates that synthetic jet is well suit for reducing the hysteresis loop and improving the maximum lift, and it is found that the combination of synthetic jets located at 12%c and 62%c from the leading edge is an optimum control strategy.