本文采用压强极小积分有限元法计算了NACA 0012翼型的跨音速流场。出发方程为全速位方程。
The transonic flow field around NACA 0012 airfoil is calculated by finite element method from pressure minimum integration, full potential equation being used.
求解全三维N-S方程，通过高分辨率格式提高跨音速流场计算的准确性，利用 LU-SGS隐式解法加快计算收敛速度。
Three dimensional Navier-Stokes equations were solved. The accuracy was improved with a high-resolution scheme. And the convergence was speeded up by the use of LU-SGS implicit method.
分别对可压缩叶栅流场的亚音速和跨音速流动进行了数值模拟计算。
Some cases of compressible flow as well as incompressible flow are presented.
提出了一种可解决超音速、亚音速、跨音速、冲击波共存的流场计算方法，即变形流体网格两步法。
The paper presents a new computational method named two steps various shape FLIC method, applied for the existence of the supersonic , sub critical sonic , transonic, shock wave.
二维跨音速叶栅流场的计算是在无粘时间相关法计算程序的基础上采用无粘-边界层迭代而得。
An inviscid-viscous interaction method based on the inviscid time marching computer code has been employed to calculate the transonic flow field of two dimensional cascade.
对某双级跨音速风扇及五级压气机流场进行了计算，双级风扇各状态的计算结果与实验数据吻合较好。
Numerical calculations were performed on a two-stage transonic fan and a five-stage compressor. The two-stage fan flow predictions show a good agreement with experimental data.
计算得到了NASA37号低展弦比、跨音速轴流压气机级70％设计转速下的全工况性能曲线，并重点分析了其中一些典型工况下的内部流场。
The overall performance for NASA 37 low-aspect ratio compressor stage at 70% design rotating speed was obtained and the internal flow fields at typical operating conditions were emphatically analyzed.
作为应用实例，本文将自适应网格用于二维无粘跨音速叶栅流场计算。
As an application example, the 2-d inviscid transonic cascade flow is solved by using adaptive grids.
作为应用实例，本文将自适应网格用于二维无粘跨音速叶栅流场计算。
As an application example, the 2-d inviscid transonic cascade flow is solved by using adaptive grids.
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