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基于RANS方程,通过刚性动网格技术实现对翼型和机翼典型运动模式的描述,采用双时间推进方法和Roe空间离散格式对流场求解,构建了一个非定常气动计算平台;以NACA0012翼型为算例进行了动态数值模拟可信度验证。数值模拟结果与试验数据吻合较好,升力和俯仰力矩的最大计算误差分别为3%和10%,表明了该平台的可靠性。另外,还数值模拟了M6机翼的动态非定常流场,并分析了两种湍流模型对非定常流场激波的捕捉能力。结果表明非定常流动中S-A湍流模型对激波的捕捉较B-L模型更敏感。文中开发的非定常计算平台对进一步解决三维复杂流场的流动问题有很高的工程应用价值。
Based on the RANS equation, the description of the typical aerodynamic model of airfoil and wing is achieved by using rigid mesh technique. The unsteady aerodynamic calculation platform is constructed by using the dual-time propulsion method and Roe spatial discretization scheme. A NACA0012 wing For the example, the dynamic numerical simulation reliability verification is carried out. The numerical simulation results agree well with the experimental data, and the maximum calculation errors of lift and pitching moments are 3% and 10%, respectively, indicating the reliability of this platform. In addition, the numerical simulation of the dynamic unsteady flow field of M6 wing is also analyzed. The ability of two turbulence models to capture unsteady flow shocks is analyzed. The results show that S-A turbulence model in unsteady flow is more sensitive to shock wave than B-L model. The unsteady calculation platform developed in this paper has high engineering application value to further solve the flow problem of three-dimensional complex flow field.