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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。
The propeller rotating slipstream passing other parts of the aircraft will change the aerodynamic performance of the aircraft in varying degrees. The analysis of the characteristics of the propeller slipstream flow field is very important in the design of the propeller aircraft. Three-dimensional solid numerical simulation of a light propeller flow field, under the design conditions (sailing speed of 66.889 m / s, speed of 2575 r / min) using the full structure of the grid, solving Navier-Stokes (N-S) equation. Through the verification of the grid dependence, 12 million grids were selected to analyze the three-dimensional flow phenomenon and the flow field and the vortex field structure in the propeller slipstream. Comparing with the theoretical calculation results of the strip, it is confirmed that the shrinkage of the slipstream area is small for the light-load propeller. The vortex structure of the slipstream area is mainly composed of the vortex band of the propeller shaft area and the vortex cylinder model of the tip area. The axial velocity, radial velocity and radial velocity coefficient in the slip surface cross section after 0.6R downstream from the plane of rotation of the propeller agree well with the Prandtl’s blade tip correction results. The correctness of the theory of the slice, but also for the power disk model provides a scientific basis for the amendment.