自适应翼型的计算和分析

Computation and analysis of an adaptive airfoil

计算并讨论了不同马赫数 (Ma)和攻角 (α)下简化的自适应翼型的舵面偏转角的规律。计算中采用代数方法生成计算网络 ,用有限体积法离散二维可压缩流动的 Euler方程 ,采用了矢通量分裂 Van- leer格式离散无粘通量 ,用隐式的时间积分和多重网格加速收敛。用数值优化方法取得自适应翼型最优的舵面偏角 ,并计算其气动特性。为验证自适应翼型增益的效果 ,计算了双目标优化翼型的气动特性。本文计算了对称圆弧翼型和NACA 6 5 A0 0 6翼型。计算结果表明 。

The deflection angles of a simplified adaptive airfoil's control surfaces are calculated at different conditions of Ma and α.In the calculation computational grid is generated by an algebraic method and 2D compressible Euler equations are solved by a finite volume method.The inviscid flux terms are discritized by using Van leer's scheme.Implicit time integration and a multigrid acceleration technique are used.An optimization method is used to obtain deflection angle of control surface and the aerodynamic efficiency of airfoil is calculated.The aerodynamic efficiency is compared with bi objective optimization airfoil's,to identify the advantage of adaptive airfoil.Numerical results of symmetric arc airfoil and NACA65A006 airfoil show that aerodynamic efficiency of adaptive airfoil is better than that of bi objective optimization airfoil.