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研究模型振动对风洞实验结果的影响对于修正风洞实验数据和加深空气动力学的理解具有重要的现实意义。基于k-ω的SST两方程湍流模型,在时间域求解雷诺平均N-S方程,研究了模型振动在不同迎角下流场和气动力的变化规律。结果表明:模型振动在小迎角条件下对气动力测量结果几乎没有影响,但在大迎角存在一定分离的条件下,可以引起分离涡的非线性演化,导致气动力平均值的改变,从而引起风洞气动力测量值的分散性。结论从物理机理上解释了大迎角风洞实验的重复性和数据分散性。
It is of great practical significance to study the influence of model vibration on the experimental results of wind tunnel in order to correct wind tunnel experimental data and deepen the understanding of aerodynamics. Based on the k-ω SST two-equation turbulence model, the Renault average N-S equation is solved in the time domain, and the variation of the flow field and the aerodynamic force of the model vibration at different angles of attack are studied. The results show that the model vibration has little effect on the aerodynamic measurements at small angles of attack, but under certain separation conditions at high angles of attack, the nonlinear evolution of the separation vortex can be induced, resulting in the change of the average aerodynamic force Wind tunnel aerodynamic measurements caused by dispersion. The conclusions explain the repeatability and data dispersion of the wind tunnel experiment at high incidence angle from the physical mechanism.