摘要
螺旋桨旋转的滑流掠过飞机的其他部件将使飞机的气动性能有不同程度的改变,对螺旋桨滑流流场特性的分析在对螺旋桨飞机设计中十分重要。三维实体数值模拟某轻栽螺旋桨流场,在设计工况下(航行速度66.889 m/s,转速2 575 r/min)采用全结构网格,求解Navier-Stokes(N-S)方程。通过对网格依赖性的验证,计算结果选取了1200万网格,深入分析了螺旋桨滑流区三维流动现象及其流场和涡场结构。通过与片条理论计算结果相比,证实了对于轻载螺旋桨,滑流区侧收缩小;滑流区的涡系结构主要由桨轴区的涡带和桨尖区的涡柱体模型组成;在距螺旋桨旋转平面下游0.6R以后的滑流区横截面上,轴向、环向、径向诱导速度系数用片条理论和Prandtl的桨尖修正结果与三维实体数值模拟结果吻合良好,验证了片条理论的正确性,同时也为动力盘模型的修正提供了科学依据。
When the revolving slipstream fly past the other parts of aircraft, it will make different degree of changes to the drag/lift property and stability to the aircraft This paper made numerical research on three dimensional flow field of a low loaded propeller. Under design conditions （ headway 66. 889 m/s, revolving velocity 2 575 rpm）, the Slipstream flow field of a Propeller is solved by RANS e- quations with structured mesh. Through verification of reliability to mesh, the mesh has chose 12 million mesh. The numerical result consists of the flow field and vortex field in the propeller slipstream. With comparison to the calculation result of standard strip theory, it is shown that for light load propeller with the side small contraction of slipstream, the vortex system structure of slipstream is com- prised of vortex zone within the propeller axis and vortex cylinder model of the blade tip; in the slipstream cross section after 0. 6R a- way from downstream of propeller rotation plane, the axial, circular and radial induced velocity coefficient by standard strip theory and Prandtl＇s blade tip corrected result is in consistent with the result of three dimensional flows numerical simulation. It verified the correct- ness of standard strip theory and also provided scientific basis for the correction of actuator disk model
出处
《控制工程》
CSCD
北大核心
2012年第5期836-840,共5页
Control Engineering of China
基金
航空科学基金项目(20102351023)
关键词
数值模拟
滑流
螺旋桨
片条理论
Prandtl修正
numerical simulation
slipstream
propeller
standard strip theory
Prandtl correction
