面向飞行器概念设计的动网格技术

Dynamic grid technology for aircraft conceptual design

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 dynamic grid methods （spring smooth approximation method and local remeshing method） and the function/shape function method, according to the facts that the program and the parameters change frequently at the phase of aircraft conceptual design, a dynamic grid method is proposed for the shape of the 2D airfoil. The method passes the changed boundary information to the grid, so that the grid is changed accordingly. Compared with the commonly used dynamic grid method, this method has better strength and resilience of the parameters performance, so the grid is generated fast. NACA 2415 airfoil, which adopts the ＂class function＂ and ＂shape function＂ translation technique （CST）, is simulated in the case of low-speed turbulent flow under different angles of attack. The results show that the proposed dynamic grid technique can better simulate the flow characteristics of the airfoil and draw airfoil aerodynamic coefficients more accurately. The technique has good application value for parameter determination at the phase of aircraft conceptual design.