亚临界情况下翼型的非线性压缩性修正

 本文从有限基本解方法出发,介绍一种计算亚音速流中非线性压缩性效应的方法。采用逐步逼近的办法,可以把有限基本解方法推广到求解非线性的无粘可压流体,从而为非线性方程的求解提供了新的途径。 编制了FORTRAN语言程序。与精确解和其他理论值的比较表明,结果比传统的有限差分法好,尤其是在翼型头部。

CALCULATION OF NONLINEAR COMPRESSIBILITY EFFECTS OF AIRFOILS IN SUBCRITICAL CONDITIONS

A method to calculate nonlinear compressibility effects of airfoils in subsonic flow based on the method of finite elementary solution （MFES） is presented. Using the progressive iterative, the method allows direct extension of MFES to nonlinear inviscid compressible flow. Thus it provides a new approach to the solution of the nonlinear equations.A computer program was completed in FORTRAN IV. The comparison of the results obtained with those of exact and other theoretical solutions shows superiority of this method to the ordinary method of finite difference, especially in the airfoil nose region.