CFD在飞翼标模支撑干扰影响研究中的应用

支撑干扰修正一直是风洞试验的一个重点和难点，特别是对于尾部扁平的飞翼布局飞行器，阻力和俯仰力矩是一个小量，进行风洞试验时，尾部需要局部放大，对阻力和俯仰力矩的影响相对较大，这就使得风洞试验时对支撑影响修正方法提出了更高的要求。本文采用CFD数值模拟手段针对小展弦比飞翼标模开展了网格收敛性和支撑干扰影响研究，分析了尾支撑对飞翼气动特性、压力分布和流场结构的影响，为进一步开展风洞试验的支撑干扰修正提供了依据。在典型工况下，支撑干扰会导致升力系数减小，阻力系数减小，抬头力矩增大；试验模型后体放大和支撑存在会导致飞翼标模上表面压力增大，激波强度变弱，尾部分离区域减小。

Application of CFD in the investigation on support interference of flying-wing calibration model

Support interference correction has always been a key and difficult problem in wind tunnel test. Especially for the flying-wing aircraft with flat tail,the drag and pitch moment are of a small amount. When a wind tunnel test is carried out,the tail needs to be enlarged locally,and the influence on the drag and pitch moment is relatively large,which makes higher requirements for the correction method of support interference.CFD method is used to study the effect of grid convergence and support interference on the low-aspect-ratio flying-wing model.The influence of support on the aerodynamic characteristics,pressure distribution and flow field structure of the flying-wing is analyzed.The results provide a basis for support interference correction in wind tunnel test.Under the typical condition,support interference will lead to a decrease in lift coefficient and drag coefficient,and an increase in lift moment.The magnification of rear body of the test model and the support interference will increase the pressure on the up surface of flying-wing model,weaken the shock intensity and decrease the separation area of the rear body.