论文部分内容阅读
采用SST两方程湍流模型,通过求解非定常Navier-Stokes(N-S)方程,对T型尾翼风洞实验流场进行了模拟,分析了保护装置对T型尾翼风洞实验流场的影响,研究了保护装置几何外形和保护装置基座后移距离对流场影响。通过对平尾气动力的分析以及对非定常流场的对比,可以得出:采用NACA系列翼型对基座进行气动整流后,基座两侧局部超声速区显著减小,局部激波减弱甚至消失,流场品质得到改善。且采用NACA0010翼型对基座修形后的结果最理想。随着保护装置基座后移距离的增加,平尾气动力均方根值和波动值先是急剧减小,达到0.85倍平均气动弦长后开始有所增大,在2.45～4.05倍平均气动弦长范围基本不再变化,稳定到单独T型尾翼模型相应系数1倍左右。此结论对T型尾翼风洞颤振实验保护装置设计具有一定的指导意义。
The SST two-equation turbulence model was used to simulate the experimental T-shaped tail wind tunnel flow field by solving the unsteady Navier-Stokes (NS) equations. The influence of the protection device on the T-shaped tail wind tunnel experimental flow field was studied. The influence of the geometric shape of the protective device and the distance of the backrest of the protective device on the flow field. By analyzing the dynamic of tail gas and comparing with the unsteady flow field, it can be concluded that the aerodynamic rectification of the base with NACA series airfoils results in a significant reduction of the local supersonic velocity zones on both sides of the base, and the local shock waves weaken or even disappear , The quality of flow field is improved. The NACA0010 airfoil has the best results on the base. With the increase of the back distance of the protective device base, the root mean square value and fluctuating value of the tail gas dynamics decrease sharply first, reaching an average pneumatic chord length of 0.85 times and then increasing. At 2.45 to 4.05 times the average pneumatic chord length The range of basic no longer change, stable to single T-tail model corresponding coefficient about 1 times. This conclusion is of guiding significance for the design of T-shaped tail wind tunnel flutter experimental protection device.