前缘小翼及开槽对扇翼气动性能影响分析
发布时间：2019-06-02 11:02
【摘要】：扇翼飞行器通过旋转机翼前缘上部的横流风扇使扇翼飞行器同时获得推力和高升力。由于升力和推力的产生都依赖于横流风扇旋转在机翼弧形段内形成的偏心涡,使得升力和推力之间有较强的耦合关系。单独改变升力或者推力就变得十分困难,降低了扇翼飞行器的操纵性。经过分析,扇翼机翼各几何参数中前缘开口角对气动性能的影响最大。通过在机翼前缘弧形段添加前缘小翼和开槽,可以改变前缘开口角的尺寸,从而改变来流进入横流风扇的方向和流量,进而改变扇翼的升力和推力,实现升推力的部分解耦。本文采用非定常数值模拟方法分析二维扇翼流场,初步研究了前缘小翼及前缘开槽对扇翼气动特性的影响。具体研究内容如下:本文首先介绍了国内外对扇翼气动性能分析的研究现状;其次,建立基于Navier-Stokes方程的扇翼气动性能分析的数值模拟方法,该方法采用分区网格划分技术、滑移网格技术和RNG k??湍流模型;采用该方法分析前缘开口角、前缘弧形槽间隙、横流风扇叶片安装角等对前缘小翼和前缘开槽设计有影响的几何参数,建立基准模型并设计小翼和开槽尺寸;然后,对比基准模型与前缘小翼对扇翼气动性能的影响,分析不同小翼安装角、不同小翼数目对气动性能的影响;最后,对比基准模型与前缘开槽对扇翼气动性能的影响,分析开槽尺寸、开槽数目、开槽位置对扇翼气动性能的影响,得出了一些有意义的结论。
[Abstract]:The fan-wing aircraft obtains both thrust and high lift by rotating the crossflow fan at the top of the leading edge of the wing. Because the generation of lift and thrust depends on the eccentric vortex formed by the rotation of crossflow fan in the arc section of the wing, there is a strong coupling relationship between lift and thrust. Changing lift or thrust alone becomes very difficult, reducing the maneuverability of fan-wing aircraft. Through analysis, the front edge opening angle has the greatest influence on the pneumatic performance among the geometric parameters of the fan wing. By adding the leading wing and slotting to the arc section of the leading edge of the wing, the size of the opening angle of the leading edge can be changed, and the direction and flow rate of the incoming flow into the crossflow fan can be changed, and then the lift and thrust of the fan can be changed to realize the partial decoupling of the lifting thrust. In this paper, the non-steady numerical simulation method is used to analyze the flow field of two-dimensional fan wing, and the influence of front edge small wing and front edge slotting on the aerodynamic characteristics of fan wing is studied. The specific research contents are as follows: firstly, the research status of fan aerodynamic performance analysis at home and abroad is introduced. Secondly, the numerical simulation method of fan wing aerodynamic performance analysis based on Navier-Stokes equation is established, which adopts partition grid division technique, slip grid technique and RNG k? The turbulence model is used to analyze the geometric parameters which have influence on the slotting design of the leading wing and the leading edge, such as the opening angle of the leading edge, the arc slot clearance of the leading edge and the installation angle of the cross flow fan blade, and the reference model is established and the size of the wing and slotted is designed. Then, the influence of the reference model and the leading edge wing on the aerodynamic performance of the fan wing is compared, and the effects of different installation angles and the number of small wings on the pneumatic performance of the fan wing are analyzed. Finally, the influence of the reference model and the leading edge slotting on the aerodynamic performance of the fan wing is compared, and the effects of slotting size, slotting number and slotting position on the aerodynamic performance of the fan wing are analyzed, and some meaningful conclusions are obtained.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V211
本文编号：2491043
[Abstract]:The fan-wing aircraft obtains both thrust and high lift by rotating the crossflow fan at the top of the leading edge of the wing. Because the generation of lift and thrust depends on the eccentric vortex formed by the rotation of crossflow fan in the arc section of the wing, there is a strong coupling relationship between lift and thrust. Changing lift or thrust alone becomes very difficult, reducing the maneuverability of fan-wing aircraft. Through analysis, the front edge opening angle has the greatest influence on the pneumatic performance among the geometric parameters of the fan wing. By adding the leading wing and slotting to the arc section of the leading edge of the wing, the size of the opening angle of the leading edge can be changed, and the direction and flow rate of the incoming flow into the crossflow fan can be changed, and then the lift and thrust of the fan can be changed to realize the partial decoupling of the lifting thrust. In this paper, the non-steady numerical simulation method is used to analyze the flow field of two-dimensional fan wing, and the influence of front edge small wing and front edge slotting on the aerodynamic characteristics of fan wing is studied. The specific research contents are as follows: firstly, the research status of fan aerodynamic performance analysis at home and abroad is introduced. Secondly, the numerical simulation method of fan wing aerodynamic performance analysis based on Navier-Stokes equation is established, which adopts partition grid division technique, slip grid technique and RNG k? The turbulence model is used to analyze the geometric parameters which have influence on the slotting design of the leading wing and the leading edge, such as the opening angle of the leading edge, the arc slot clearance of the leading edge and the installation angle of the cross flow fan blade, and the reference model is established and the size of the wing and slotted is designed. Then, the influence of the reference model and the leading edge wing on the aerodynamic performance of the fan wing is compared, and the effects of different installation angles and the number of small wings on the pneumatic performance of the fan wing are analyzed. Finally, the influence of the reference model and the leading edge slotting on the aerodynamic performance of the fan wing is compared, and the effects of slotting size, slotting number and slotting position on the aerodynamic performance of the fan wing are analyzed, and some meaningful conclusions are obtained.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V211
【引证文献】
相关期刊论文 前1条
1 林超希;张文宇;马超;;一种两轴和四轴扇翼飞行器的设计[J];科技风;2017年13期
，本文编号：2491043
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