NACA-65-0012机翼的非定常反问题解

THE SOLUTION OF UNSTEADY INVERSE PROBLEM FOR NACA-65-0012 AIRFOIL

利用有限差分法解非定常欧拉方程是振荡机翼非定常气动反问题的一种求解方法。本文重点讨论了非定常气动反问题求解的计算方案与反问题固壁边界条件的处理,编写了相应的计算程序。本文以绕前缘点做小幅俯仰周期振动的NACA-65-0012翼型为初始机翼,在振幅分别为0°、2．51°的条件下进行了气动反问题计算,经过多次迭代后计算翼型的压力分布基本与目标压力吻合,这表明本文的反问题求解方案、反问题边界处理及计算程序是可行的。

It is one of approaches for unsteady inverse problems of oscillating airfoil to solve unsteady Eluer equations with finite difference method. The solution strategy and solid boundary condition for unsteady inverse problem are discussed in the paper, and the code is accomplished. The solution of inverse problems for oscillating airfoil with swing angle 0° and 2.51° is carried out. The initial airfoil used in paper is NACA-65-0012 airfoil which pitches around its leading edge. The distribution of pressure over numerical airfoil coincides with the design pressure well after several iterations. The result indicates the strategy and solid boundary condition in the paper are reliable.