【摘要】 使用解析形状函数法和参数化翼型表示方法,将求解绕翼型流场的N S方程解与优化方法相结合,可设计出新的高升阻比翼型。计算结果表明,设计的新翼型满足设计要求,且获得比原始翼型高得多的升阻比,翼型设计方法是实用的。参数化翼型表示法比解析形状函数法对给定的初始翼型离散数据的准确度影响更小,更适合用于新翼型的设计。更多还原

【Abstract】 The combination of a N-S equation flow solver with a nonlinear optimization method is used to design a new airfoil with high ratio of lift over drag. The finite volume method is used to discritize the N-S equation. AUSM+ scheme is used to discritize inviscid flux terms. Central difference scheme is used to discritize viscous flux terms and Runge-Kutta time-stepping method is used in the time integration. The turbulent viscous effect is calculated using the Baldmin-Lomax model. Using B Spline to transfinite interpolation generate grid. Optimization method is Powell method. Airfoil shapes in design process are represented by both methods of analytic shape function and parameterized function. Numerical results show that designed airfoils meet the assigned requirements and have higher ratio of lift over drag than that of the initial ones. The airfoil design method is effective and roubst. The parameterized function method is less influenced by the given accuracy of description data of initial airfoil than the analytic shape function method. So the parameterized function method is more suitable to new airfoil design.更多还原