An engineering approach is presented to analyse the asymmetric blade thrust effect with the help of analytical and semi-empirical methods. It is shown that the contribution of the asymmetric blade thrust effect in the lateral-directional stability of multi-engine propeller-driven aircraft is significant particularly in critical flight conditions with one engine out of service. Also, in some cases where the engines are rotating in one direction, the asymmetric blade effect has substantial effects on the handling qualities of the aircraft even in normal flight conditions. Overall, due to the significant contribution of this phenomenon in the lateral-directional stability of propeller-driven airplanes, it is important to consider it in the design of the vertical stabilizer and rudder. The resulting analytical method has been used to determine the vertical tail incident angle and desired rudder deflection in accordance with the most critical flight condition for two different cases and validated to ensure the accuracy of the result. In this work, the aerodynamic coefficients as well as the stability and control derivatives have been predicted using analytical and semi-empirical methods validated for light aircraft.

提出了一种借助分析和半经验方法来分析非对称叶片推力效应的工程方法。结果表明，非对称叶片推力效应对多发螺旋桨飞机的横向稳定性的贡献是显着的，尤其是在一台发动机停用的临界飞行条件下。此外，在发动机沿一个方向旋转的某些情况下，即使在正常飞行条件下，不对称叶片效应也会对飞机的操纵质量产生重大影响。总体而言，由于这种现象对螺旋桨驱动飞机的横向稳定性有重大贡献，因此在设计垂直安定面和方向舵时考虑这一点很重要。所得分析方法已用于根据两种不同情况下最关键的飞行条件确定垂直尾翼入射角和所需舵偏转，并进行验证以确保结果的准确性。在这项工作中，空气动力学系数以及稳定性和控制导数已经使用针对轻型飞机验证的分析和半经验方法进行了预测。