|Alternative Title||Research on Aerodynamic Characteristics of Fan Wing Lift Device|
|Place of Conferral||北京|
|Keyword||扇翼 Cfd 非定常流场 偏心涡 旋转双扇翼|
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.
|陈申. 扇翼升力装置气动特性研究[D]. 北京. 中国科学院大学,2018.|
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