关键设计参数对摆线桨气动性能影响

以西北工业大学自行研制的摆线桨飞行器为研究对象,对简化的二维摆线桨模型进行了非定常数值模拟.在数值模拟模块中,桨叶的公转及俯仰振荡运动采用弹簧近似光滑模型和局部重划模型相结合的动网格技术来处理.重点研究了关键设计参数对摆线桨气动性能的影响,结果表明:随着桨叶数的增加,悬停气动效率提高;随着翼型厚度增加,推力变大,气动功耗减小;桨叶俯仰轴位置位于桨叶弦向中部位置时的功率载荷最大,悬停气动效率最高;随着最大俯仰角增大,气动功耗逐渐增加,悬停气动效率降低;当桨叶上、下半周最大俯仰角之和一定时,采用上半周最大俯仰角小的设置时,推力和气动功耗较大,悬停气动效率也更高.

Influence of key design parameters on aerodynamics performance of cycloidal propeller

The two-dimensional cycloidal propeller model was simplified from a cycloidal propeller aircraft developed by Northwestern Polytechnical University. The dynamic mesh method of spring-based smoothing and local remeshing was adopted to achieve blades' rotating and pitching movement in the unsteady numerical simulation. The influence of the key design parameters on aerodynamics performance of cycloidal propeller was researched. The result shows that, the aerodynamics efficiency of hovering status is found higher with the increase of blade number; when the airfoil thickness increases, the thrust level is higher while the aerodynamics power is lower; the aerodynamics efficiency of hovering status and power loading reach highest when the pitching axis is located at middle chord length of blade; when the maxium pitching angle is higher, the aerodynamics power becomes larger and aerodynamics efficiency of hovering status is lower; and when the sum of maxium pitching angle at top position and maxium pitching angle at bottom position is constant, the thrust, aerodynamics power and aerodynamics efficiency of hovering status are higher if the maxium pitching angle at top position is small.