梯形翼风洞试验模型数值模拟技术

基于雷诺平均Navier-Stokes (RANS)方程和结构网格技术,采用二阶空间离散精度的MUSCL格式,并结合k-ω剪切应力输运(SST)两方程湍流模型和γ-Re_θ转捩模型,研究了梯形翼风洞试验模型中前缘缝翼、后缘襟翼连接装置对气动特性的影响。简要介绍了本文采用的计算方法;介绍了梯形翼的风洞试验模型及风洞试验结果;在网格收敛性研究的基础上,采用"全湍流"方式和转捩模型研究了梯形翼试验模型连接装置对气动特性的影响。通过与不带连接装置的计算结果的对比,采用"全湍流"模拟方式,计算模型中考虑试验模型的连接装置引起升力系数下降、阻力系数下降、低头力矩减小以及失速迎角提前;通过与试验数据的对比,进一步考虑转捩影响可以提高梯形翼风洞试验模型气动特性的计算结果与试验结果的吻合程度,梯形翼风洞试验模型失速迎角附近的气动特性数值模拟技术还需要进一步的研究。

Numerical simulation of trapezoidal wing wind tunnel model

Based on the Reynolds-averaged Navier-Stokes(RANS) equations and structured grid technology, with second-order MUSCL scheme, combined with k-ω shear stress transport (SST) turbulence model and γ-Re_θ transition model, the influence of the support brackets included in the wind tunnel model on the aerodynamic characteristics of the high lift trapezoidal wing (Trap wing) is studied. Firstly, the numerical methods are introduced briefly. Then, the wind tunnel models of the Trap wing configuration and the experimental activities are described. And then, on the basis of previous grid convergence study, the influences of the support brackets included in the wind tunnel model on the aerodynamic characteristics of the Trip wing configuration are studied with "fully turbulent" and transition modes. Finally, the conclusions are presented. Compared with the bracket-off numerical results, with "fully turbulent" mode, the support brackets decrease the lift coefficients, drag coefficients and nose-down momentum coefficient, resulting in the earlier stall angle. Compared with the experimental data, the bracket-on numerical results with the transition model are in very good agreement with test data and further study on the simulation technology of aerodynamic characteristics near the stall angle for Trap wing wind tunnel model is needed.