小展弦比飞翼标模 FL-2风洞跨声速开孔壁干扰特性修正研究

摘要

In order to meet the elaborateness requirements of modern wind tunnel testing and improve the accuracy of wind tunnel test data,the nonlinear method of transonic porous wall in-terference corrections based on wall pressure is developed.The measured wall pressure informa-tion is adopted to construct the porous wall boundary conditions,and the flow field around the test model in the wind tunnel is simulated numerically with the N-S equations.Unlike the linear correction methods,this method can be used for a variety of complex shapes of the aircrafts to correct the porous wall interference in the subsonic or transonic wind tunnel.The characteristics of wall interference corrections is studied combining with test data of the low aspect ratio flying wing model conducted in the FL-2 wind tunnel.The results indicate that the wall interference has a rising trend with the Mach number increasing,the interference reaches to the maximum at about Ma=1.0,and the corrected results of the FL-2 wind tunnel test data are in good agreement with the test results of the FL-26 wind tunnel approximately without interference.%为了满足现代风洞试验精细化要求，提高风洞试验数据精准度，开展跨声速开孔壁洞壁干扰修正方法研究。本文利用实测壁压信息构造开孔壁边界条件，通过求解 N-S 方程，模拟试验模型在风洞中的绕流场，建立基于壁压信息的跨声速洞壁干扰非线性修正方法。不同于线性修正方法，本方法可用于各种复杂外形飞行器的亚、跨声速开孔壁洞壁干扰修正，结合小展弦比飞翼标模风洞试验数据，对其在 FL-2风洞试验数据开展洞壁干扰特性研究。洞壁干扰修正结果表明，洞壁干扰量随马赫数变化呈增长趋势，Ma ＝1．0左右达最大，经过修正的 FL-2风洞的跨声速试验结果，与 FL-26风洞近似无干扰试验结果吻合良好。