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在弹簧近似光滑法和局部网格重构法两种动网格方法的基础上,结合类型函数/形状函数方法,针对飞行器概念设计阶段方案多变、参数变化快的特点,对二元机翼随参数变化的翼型提出了相适应的动网格方法。该方法根据参数的影响,将变动的边界信息传递到网格上,网格随之迭代变化。相对于常用动网格方法,该方法具有更强的参数表现力和适应力,使得网格生成更快速。对类型函数/形状函数转换方法(CST)拟合的NACA2415翼型在不同迎角情况下的低速湍流流动进行了数值模拟。计算结果表明,该动网格技术较好地模拟出了翼型的流动特性,较准确地得出了翼型的气动力系数,对飞行器概念设计阶段的参数确定具有实用价值,显示了该动网格方法的准确性和便捷性。
Based on the two moving grid methods of spring approximation smoothing method and local mesh reconstruction method, combined with the type function / shape function method, aiming at the characteristics of the changing design of the aircraft conceptual design stage and the rapid change of parameters, The airfoils with varying parameters proposed a moving mesh method. According to the influence of parameters, the method transfers the changed boundary information to the grid, and the grid changes iteratively. Compared with the commonly used moving mesh method, this method has stronger parameter expression and adaptability, which makes the mesh generation faster. NACA2415 airfoil fitted with type function / shape function transformation method (CST) was numerically simulated under different angles of attack for low velocity turbulent flow. The calculation results show that the moving grid technology can simulate the flow characteristics of the airfoils and obtain the aerodynamic coefficient of the airfoils more accurately, which has practical value for the parameter determination in the conceptual design phase of the aircraft. Accuracy and convenience of grid methods.