基于线性涡模型的风洞孔壁干扰特性分析

发展了一种适用于二元翼型试验洞壁干扰特性的评估和修正方法.基于Prandtl-Glauert速度势方程和布置在模型及洞壁表面的线性涡，采用迭代方法计算了风洞孔壁对翼型表面压力分布特性的影响，分析了不同孔壁透气特性参数的影响规律和量值，利用与国外参考结果及风洞试验结果的对比确定了该方法的准确性.结果表明，孔壁对翼型绕流的影响主要反映在上翼面吸力峰和最大厚度位置之间，使压力系数减小，积分后的升力系数降低，且随着孔壁透气特性参数的增大，洞壁干扰由实壁特性向开口特性发展，洞壁干扰、影响量急剧增大.与传统方法相比，该方法计算快速，结果可靠，同时具备试验前评估的能力，可用于亚临界范围内翼型表面压力的快速估算，以及翼型试验的洞壁干扰修正.

Interference Characteristics Analysis of Wind Tunnel Perforated Wall Based on the Linear Vortex Model

An estimation and correction method of perforated wall-induced interference characteristics for 2D airfoils was proposed. Based on the Prandtl-Glauert velocity potential equation and linear vortices arranged on the surfaces of the airfoil and tunnel walls, the effects of the perforated wind tunnel wall on pressure distributions on the airfoil surface were solved iteratively to analyze influences of air permeability parameters of the perforated wall. Previous reference data and wind tunnel test results were used for comparison to validate the accuracy of the proposed calculation method. The comparison shows that, the effects of the perforated tunnel walls on the flow around the airfoil mainly act on the upper surface between the suction peak and the maximum thickness, and lead to lower pressure coefficients and decreased integrated lift coefficients. With the increase of the air permeability parameter of the perforated wall, the wall interference characteristics develop from the solid wall to the open boundary sharply. With good efficiency and reliability, the proposed method applies to quick estimation of the pressure on the airfoil surface in the subcritical range, and evaluation of the wall interference in the 2D airfoil tests.