本文提供了一种能有效计算螺旋桨性能的方法。方法的特点在于 :(1)边界条件中利用了中弧面上的局部斜率以代替平面边界条件 ,使本方法适用于具有较大弯度翼型的螺旋桨 ;(2 )用近似解析式与数值积分结合起来计算螺旋形尾涡产生的诱导速度 ,在保证精度的条件下 ,使计算工作量降低到原有的 10 % ;(3)利用翼型的升阻特性考虑翼型阻力及压缩性影响。利用本方法对某型飞机的螺旋桨进行了计算 ,并与实验数据作了比较 ,在进距比不太小的情况下 ,计算结果与实验数据符合很好。 This article provides a way to efficiently calculate propeller performance. The method is characterized by: (1) using the local slope on the camber surface in the boundary conditions in place of the plane boundary conditions, making the method suitable for a propeller with a larger camber airfoil; (2) using approximate analytical expressions and numerical integration Combining to calculate the induced velocity of spiral vortex eddy, under the condition of ensuring the accuracy, the calculation workload is reduced to 10% of the original. (3) The aerodynamic resistance and compressibility of aerofoil are considered considering the lift resistance of airfoil. Using this method, the propeller of a certain type of aircraft is calculated and compared with the experimental data. When the pitch ratio is not too small, the calculated results are in good agreement with the experimental data.