基于N-S方程的翼型实验侧壁边界层控制

Side-wall boundary layer removal at airfoil test based on Navier-Stokes equations

使用三维可压、雷诺平均N-S方程数值计算了NACA0012翼型在二元翼型风洞中不同迎角和马赫数状态下的压力分布,改进了划分计算网格的Hilgenstock方法,发展了一种利用N S方程计算结果,来确定翼型实验中为消除侧壁边界层干扰的抽气压力的方法。通过比较利用本文介绍的方法计算的NACA0012翼型实验侧壁抽气压力和相同状态下,在西北工业大学0.3m×0.1m二维跨音速风洞中经油流显示证明为合适的抽气压力,结果表明该方法是可行的。

Pressure distribution of NACA 0012 airfoil mounted in two-dimensional wind-tunnel at given angle of attack and Mach number is computed by solving three-dimensional compressible Renolds-averaged Navier-Stokes equations. Much improvement has been made in Hilgenstock's approach adopted to generate body-fitted grid by solving Poisson equations in order to decrease CPU time. A new numerical method of calculating appropriate suction pressure which is adopted in side-wall boundary removal is presented. Comparison between calculated suction pressure of NACA0012 airfoil and tested suction pressure at the same status which is proved correct by oil-flow-picture in Northwest Polytechnic University(NPU) 0.3m×01m two-dimensional transonic wind-tunnel demonstrated that the method developed in this paper is accurate and useable.