大攻角非线性问题的局部线化方法

 本文引用局部线化的概念,提出一种数值计算方法,用以研究小展弦比、大攻角带前缘或侧缘分离流机翼的双重非线性问题,即基本方程的非线性（包含了速势方程的所有二阶非线性项）和边界条件的非线性（离体涡位置不能预先给定）。该方法适用于亚临界下的所有Mach数,计算简单,工作量小。通过算例计算表明,该方法计算结果与实验值是一致的。

A NUMERICAL METHOD FOR COMPUTING THE AERODYNAMIC LOADS ON WINGS WITH SHARP-EDGE SEPARATIONS AT LARGE ANGLES OF ATTACK IN SUBCRITICAL TRANSONIC FLOWS

In this paper,a numerical method based on the nonlinear potential equation containing all the quadratic terms for computing the nonlinear aerodynamic loads on wings with sharp edge separations at large angles of attack in subcritical near-sonic flows is presented. A local linearization assumption is imposed in this method. Through an iteration procedure, the Problem with two sources of noalinearities, namely, a boundary-oriented (separated flow roll-up) and equation-oriented nonlinearity, is treated successfully. Numerical results are compared with experimental data aad are found to be in good agreement. In addition, the method is also applicable to complex wing planforms. By comparing with the finite difference methods and the method based on the integral approach, the present method appears to be economic.