基于特征正交分解翼型流场反设计方法研究

Airfoil Flow Field Reconstruction via Proper Orthogonal Decomposition

基于特征正交分解(Proper Orthogonal Decomposition,POD)方法中模态的思想,利用特征正交分解基,通过改变马赫数或迎角来得到相应的流场快照,对流场参数进行重构,基于快照范围内可以得到高精度的重构流场结果。以NACA0012翼型和RAE2822翼型为研究对象,采用POD方法对流场参数进行了重构。验证结果表明,POD方法能高效而精确地重构所需状态下的二维流场参数,并具有一定的外插能力。该方法为数值风洞、流动控制及翼型设计研究提供了理论基础。

A method for reconstructing flow fields that using proper orthogonal decomposition (POD) basis functions or modes with great reduction on the computational cost is presented.Using this approach,it is possible to construct entire aerodynamic flow fields from the knowledge of computed aerodynamic data or measured flow data specified on the aerodynamic surfaces,demon-strating a way to effectively combine experimental and computational data.There are three cases here,varying inflow Mach number to NACA0012 airfoil in subsonic region and RAE2822 airfoil in transonic region.The results demonstrate that the POD procedure could provides effectively high accurate flow fields reconstruction when just very little amount of data is known.It is a simple,effective method for digit wind tunnel,flow control,and airfoil design.