在当今社会中，随着能源问题和环境问题的日益敏感，以及航空燃料成本比重的不断增加，燃油经济性高的螺旋桨飞机重新引起了航空公司和航空工程师的关注。螺旋桨滑流会对飞机各部件的气动特性产生较大影响，但现在鲜有螺旋桨飞机在优化设计阶段考虑滑流影响。本论文的主要工作为：发展了激励盘方法，针对螺旋桨飞机进行了气动研究，发展了螺旋桨飞机的带滑流气动优化设计方法，并提高了螺旋桨飞机的巡航升阻比。 首先，本文对激励盘方法进行了详细研究，以准确快速模拟螺旋桨滑流。在二维激励盘方法的基础上，提出并构造了基于体积力的三维激励盘方法，改善了二维激励盘方法中流场存在间断、激励盘参数获取不直接的问题，滑流计算效果良好，提高了激励盘计算精度。 然后，本文对桨尖涡的诱导速度进行了推导，并在激励盘方法中加入了桨尖涡模型，使激励盘方法更加完善，进一步提高了激励盘方法的计算精度。 继而，基于激励盘方法，本文对一款双发螺旋桨飞机的气动特性进行了数值研究。研究表明，螺旋桨滑流会对机翼的载荷分布、短舱和机翼附近的流动分离、尾翼上的气动力产生影响。本文研究了短舱安装角的改变对巡航状态飞机升阻比的影响，并确定了巡航状态的最佳短舱安装角。 最后，本文将激励盘方法和气动优化设计方法结合在一起，形成了螺旋桨飞机带滑流气动优化设计平台。基于该设计平台，本文对螺旋桨飞机的机翼进行了带动力优化设计，研究了有无滑流、不同滑流方向以及不同设计变量对飞机气动特性的影响，并成功提高了飞机的巡航升阻比。

Nowadays, the energy problem and environmental problem are more and moreimportant. In aviation world, propeller aircrafts have high fuel efficiency. Thus, more aviation companies and engineers tend to focus on propeller aircrafts. Propeller slipstream can affect the aerodynamic performance of multiple aerodynamic components, but few engineers take slipstream into consideration during aircraft optimization. The key contributions of this thesis are: new actuator disc methods are developed, the aero performance of a turboprop aircraft is studied, a propeller aircraft optimization design method with slipstream is presented, and the lift-to-drag ratio of a propeller aircraft is increased. Firstly, the actuator disc method is detailed studied in this thesis, so it can be used to simulate propeller slipstream fast and accurate. Based on traditional two-dimensional actuator disc method, a three-dimensional actuator disc methodbased on volume force is developed, and it works well and the accuracy of the actuator disc method is improved. Secondly, the induced velocity of propeller tip vortex is derived, and thenthe propeller tip vortex model is added onto present actuator disc model. Thus,the actuator disc method is more complete and accurate. Thirdly, based on the actuator disc method, the aerodynamic performance ofa twin-turboprop aircraft is studied numerically. Research showed that thepropeller slipstream has influence on wingload distribution, flow separations near the wing/nacelle, and forces on the tail. Studies about how the mounting angle of the nacelles change cruising lift-to-drag ratio is carried out. Finally, the actuator disc method and the aero optimization design method are combined to realize powered optimization design of propeller aircrafts. Basedon this method, the wing of a twin-turboprop aircraft is optimized. Influence of different slipstream settings and different variables are studied. The cruising liftto-drag ratio is increased.