论文部分内容阅读
本文使用表面源汇法计算位流,然后用所得到的翼型表面上和尾迹中心线上的压力分布计算边界层和尾迹层,然后由边界层及尾迹与位流迭代计算得到低速粘性流动中翼型的气动特性。 算例计算结果与实验结果比较一致,本文的方法可用于飞机设计中翼型的选型计算,零升阻力计算及中等迎角以下的升力,阻力和力矩特性计算。 最后给出了用本方法设计的先进翼型NPU-100的实验结果,比较指出,采用新翼型将使亚临界短程飞机(对爬升特性要求较高)的气动性能得到重大改进。还指出,具有很宽低阻范围的NPU-100翼型也是良好的风机翼型。
In this paper, the surface source and sink method is used to calculate the bit-stream, and then the boundary layer and the wake layer are calculated by the pressure distribution on the surface of the airfoil and on the wake centerline. Then, the boundary layer and the wake and the bit stream are iteratively calculated to obtain the low- Airfoil aerodynamic characteristics. The calculated results are in good agreement with the experimental results. The proposed method can be used to calculate the airfoil in the aircraft design, the calculation of the zero-lift resistance and the calculation of the lift, drag and moment characteristics under medium angle of attack. Finally, the experimental results of the advanced airfoil NPU-100 designed by this method are given. It is pointed out that the new airfoil will greatly improve the aerodynamic performance of the subcritical short-range aircraft, which has higher requirements on the climbing characteristics. It is also noted that NPU-100 airfoils with a wide range of low resistance are also good fan airfoils.