摘要
以给定的压力分布或速度分布作为目标，引入目标压力分布与保角变换模H的关系，经过求解流场和变换模H的反复迭代，逐步收敛到目标压力分布，通过积分变换模H就可以得到物理平面上翼型外形（x，y）的坐标，达到设计翼型的目的。以GK72－05－12和N0．75目标压力分布为例设计出的翼型与相应翼型几何外形相当一致。
A inverse aerodynamic design technique has been presented for 2-D supercritical airfoil. The method we used is the prescribed pressure distribution in a boundary condition for the determination of the conformal mapping from the unit circle to the desired airfoil. The design examples show that the method is capable of providing satisfactory design results to supercritical airfoil.
出处
《空气动力学学报》
CSCD
北大核心
1997年第2期153-160,共8页
Acta Aerodynamica Sinica
