论文部分内容阅读
为了提高跨声速机翼气动效率,采用了基于伴随算子的优化设计方法对跨声速机翼进行了优化设计。其中,采用基于多块结构网格的流场解算器计算机翼气动力系数,采用相对应于流场解算器计算气动力系数对设计参数的导数。解算器的空间离散采用Osher格式,优化时湍流模型采用B-L模型。初始机翼设计采用参数化设计。优化设计结果表明,升阻比相对改善8.1%,从数值计算的角度表明了该方法的有效性。
In order to improve the aerodynamic efficiency of transonic wings, an optimization design based on the attendant operator is used to optimize the transonic wings. Among them, the flow field solver based on multi-block structure grid is used to calculate the aerodynamic coefficient of the wing, and the derivative of the aerodynamic coefficient to the design parameter is calculated corresponding to the flow field solver. The spatial resolution of the solver is Osher format, and the turbulence model is B-L model. Initial wing design using parametric design. The results of the optimization design show that the lift-drag ratio is relatively improved by 8.1%, which shows the effectiveness of the method from the numerical calculation point of view.