控制超临界翼型边界层分离的微型涡流发生器数值模拟

Numerical simulation of boundary layer flow separation control for supercritical wing using micro-vortex generators

本文基于任意曲线坐标系下的雷诺平均Navier-Stokes方程和Spalart-Allmaras一方程湍流模型,采用对接拼接网格技术和多重网格加速收敛技术,对安装有叶片式微型涡流发生器的超临界机翼翼身组合体进行了数值模拟,研究了微型涡流发生器的高度和弦向安装位置对超临界机翼附面层流动控制的机理以及对超临界机翼气动性能的影响规律。

In this paper,the main contents are focused on flow control mechanism of micro-vortex generators and aerodynamic performance of supercritical wing.To simulate the aerodynamic characteristics of supercritical wing using micro-vortex generators,based on the RANS equations and SA turbulent model,the numerical methods are adopted including cross-grid technology and multi-grid method.Effectiveness of micro-vortex generators heights and positions on flow control mechanism and aerodynamic performance of supercritical wing are investigated.