飞翼布局高速风洞尾支干扰试验修正技术研究

飞翼布局飞行器模型往往具有尾部扁平的结构特点，进行高速风洞尾支测力时，尾部需要局部放大，由此带来尾部畸变和尾支杆的气动干扰，直接影响对巡航效率、焦点位置以及配平迎角的预测；另外，飞翼布局飞机为改善隐身特性，取消了平尾和垂尾，侧力和偏航力矩量级比较小，模型尾部的局部变形必然会对飞机横、航向试验数据带来不利影响。本文针对某飞翼布局模型，采用风洞试验和 CFD 数值模拟相结合的手段，通过腹支撑作为辅助支撑的“两步法”获得了尾部畸变及尾支杆的纵、横向支撑干扰影响。研究结果表明：该飞翼布局模型尾部畸变支撑纵、横向支撑干扰修正结果合理、可靠，精准度较高；所建立的试验与 CFD 相结合的研究方法可以用于类似布局的试验数据修正。同时，发展的数值计算方法与风洞试验有很好的一致性，已成功应用于某飞翼布局模型尾部支撑干扰修正，已具备工程使用价值。

Investigation on the interference correction of flying wing aircraft rear sting support in high speed wind tunnel test

For the test of a flat-after-body flying wing aircraft model in high speed wind tun-nel,the after-body has to be modified to satisfied the attachment of the balance.The deformation and the means of tail support may have some effect on the aerodynamic characteristics of the air-craft,and further affect the cruising efficiency,the trimming angle and the location of the aero-dynamic center.On the other hand,there are no commonly used horizontal tail and vertical tail for a flying wing aircraft in order to reduce RCS,the interference of distorted after-body can not to be neglected compares to weak lateral controllability.With the help of CFD and test tech-nique,the distorted after-body support interference has been obtained,in which rear sting is the main support and ventral strut an auxiliary one.The research indicates that the result of the wind tunnel test is accurate and reliable,the correction method can be adopted for the similar configu-ration model test.The methods of both numerical simulation and wind tunnel tests have been used to correct tail support interference of a flying wing model successfully.