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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-Reθ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。
Based on the Reynolds-averaged Navier-Stokes (RANS) equation and the structural grid technique, the second-order spatial discrete-precision MUSCL scheme is used. Combined with k-ω shear stress transport (SST) turbulence model and γ-Reθ transition model , The effects of the leading edge slat and the trailing edge flap connecting device on the aerodynamic characteristics were studied in the trapezoidal wind tunnel test model. The calculation method adopted in this paper is introduced briefly. The wind tunnel test model of trapezoidal wing and the wind tunnel test result are introduced. Based on the study of grid convergence, the “full turbulence” mode and transition model are used to study the trapezoidal wing Influence of Test Equipment on Pneumatic Characteristics. Through the comparison with the calculation results without the connecting device, the “full turbulence” simulation was adopted. The connection device considering the test model in the model caused the decrease of the lift coefficient, the decrease of the drag coefficient, the decrease of the bowing moment and the advancement of the stalling attack angle. By comparing with the experimental data, further considering the effect of transition can improve the agreement between experimental results and aerodynamic characteristics of trapezoidal wind tunnel test model, numerical simulation technology of aerodynamic characteristics near traversing angle of attack of trapezoidal wind tunnel test model Further research