扇翼飞行器既不同于具有固定翼的传统飞机，又不同于具有多个旋转翼的直升飞机，这种飞行器通常通过在机翼前缘或后缘合理地镶嵌安装适当尺寸和长度的横流风扇，以改进绕机翼气流的流动路径和状态，从而提高机翼的升力和推力，最终使飞行器具有低速大载荷、短距起降或垂直起降的特点，提高飞行器的飞行效率，因此，这类飞行器在军事和民用领域具有广泛的应用前景。目前，国内外对这种飞行器的气动性能的研究尚处于起步阶段，仍需要进行深入的理论分析和实验研究。本论文以扇翼升力装置为研究对象，利用不可压缩Navier-Stokes方程的数值模拟分析了风扇翼流场的特点，研究了扇翼装置的升力和推力随不同计算工况及外形参数的演化规律；利用旋转的实验测试平台，开展了旋转双扇翼升力装置实验研究。具体内容如下：

作者首先介绍了扇翼类飞行器国内外的研究和发展现状，并据此确定了本文所介绍研究内容的意义和目的；其次基于非定常不可压缩Navier-Stokes方程，建立了求解扇翼二维模型流场的数值仿真方法，该方法采用SIMPLE算法求解压力速度耦合方程，采用标准k-ε湍流方程结合壁面增强函数模拟湍流，时间格式采用双时间步隐式格式；文章对相关文献提供的扇翼飞行器几何模型进行建模分析，通过将数值结果与实验结果的相互对比，验证本文所建立的数值模拟方法的正确性；本文利用和实际实验对应的二维扇翼模型，分析了风扇翼的流场特点，研究了扇翼升力装置流场随空气来流条件、横流扇转速及扇翼外形几何参数的演化特征；在此基础上，研究发现机翼前缘带翼舌的结构有利于提高扇翼升力装置的升力；在旋转的双扇翼升力装置的实验测试中，实验研究了升力与横流扇转速和旋转扇翼升力装置转动速度的对应关系，在实验中讨论了两种转动功率消耗的特点，验证了机翼前缘带翼舌的结构有利于升力提高的特点，这些数值模拟和实验研究为扇翼飞行器的设计和研制提供了理论和技术依据。

Fan-wing aircraft is both different from conventional aircrafts with fixed wings and from helicopters with multiple rotating wings. Cross-flow fans with appropriate size and length are normally installed at the leading or trailing edge of the wings of this type of aircraft. This type of wing structure is used to change the path and state of the airflow flowing around the wings to increase the lift and thrust of the wings. It brings the aircraft the characteristics of large load with low speed as well as short take-off and landing (STOL) or vertical take-off and landing(VTOL). These features greatly improve the flight efficiency of fan-wing aircraft. Therefore, this type of aircraft has broad application prospect in the military and civilian fields. At present, researches on the aerodynamic performance of fan-wing aircraft at home and abroad are still in its infancy, and in-depth theoretical analysis and experimental research are still needed. The research object of this thesis is the fan wing lift device. The characteristics of fan wing flow field are analyzed by numerical simulation of incompressible Navier-Stokes equations. The evolution of lift force and thrust of fan wing device along with different work conditions and geometric parameters is researched. The experimental research on rotating double fan wings lift device is carried out on the rotating experimental platform. The details are as follows:

The thesis firstly introduces the domestic and foreign research situation of fan-wing aircraft. According to this, the significance and aim of the article's research content are established. Based on the unsteady incompressible Navier-Stokes equations, the numerical simulation method for solving the flow field of fan wing two-dimensional model is established. In this method, SIMPLE algorithm is used to solve the pressure-velocity coupling equations. Standard k-ε turbulence equations combined with enhanced wall function are used to simulated turbulence. Dual-time stepping implicit scheme is adopted. The geometric model of the fan-wing aircraft provided by some literature is simulated in the paper. The correctness of the numerical simulation method established in this paper is verified by comparing the numerical results with the experimental results. The thesis analyzes the characteristics of flow field of fan wing corresponding to the actual experiment model. The evolution of the flow field of fan wing device along with incoming flow condition, rotate speed of the cross flow fan and geometric parameters of fan wing is researched. The study finds that the structure of the fan wing which extends certain length tongue on the leading edge of the wing helps to increase the lift. In the experimental test of the rotating double fan wings lift device, the relationship between lift force and the rotational speeds of both the cross-flow fan and the rotating double fan wings is studied. Two types of rotational powers are tested. It is verified that the structure of the fan wing which extends certain length tongue on the leading edge of the wing is conducive to improve the airfoil lift. The numerical analyses and experimental studies above provide theoretical and technical foundation for the design of fan-wing aircraft.