翼型低速动态测压试验洞壁干扰修正方法研究  

Investigations of Wind Tunnel Wall Correction Methods for Airfoil Low-speed Dynamic Pressure Measurement

作　　者：邹宏毅 焦予秦[1] 柳伟兵 ZOU Hongyi;JIAO Yuqin;LIU Weibing(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空工程进展》2021年第3期29-36,共8页Advances in Aeronautical Science and Engineering

摘　　要：翼型在风洞中进行非定常试验时,为了从试验中获得精确的气动数据,需要对风洞洞壁干扰进行修正。采用一组几何相似大小不同的NACA0012模型,在西北工业大学NF-3风洞中开展翼型低速动态测压试验;提出将相同无量纲动态参数下的不同尺度模型试验结果线性插值到0尺度求取动态试验洞壁干扰的方法,并采用风洞试验结果对动态试验洞壁干扰进行评估和修正。结果表明:本文提出的洞壁干扰修正方法符合实际需要,能够为动态试验风洞洞壁干扰修正提供参考和思路。When the airfoil is subjected to unsteady wind tunnel test,it is necessary to correct the wall interference to obtain accurate aerodynamic data from test.Using a group of NACA0012 airfoil models with same geometric similarities and different sizes,airfoil low-speed dynamic pressure measurement is carried out in NF-3 wind tunnel of Northwestern Polytechnical University.Different scale model test results are interpolated to 0 scale under the same dimensionless dynamic parameters to calculate the wall interference.The wind tunnel test results are used to evaluate and correct the wall interference of dynamic test.The results show that the proposed correction method is effective,and this method can provide references and ideas for wall interference correction.

关 键 词：NACA0012翼型 动态测压 缩减频率 线性插值 洞壁干扰修正 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]