民航飞机尾涡流场数值模拟计算研究

发布时间：2018-04-06 21:27

本文选题：尾涡流场　切入点：数值模拟　出处：《中国民航大学》2015年硕士论文

【摘要】：随着航空业的不断发展,现有的尾流安全间隔偏大,已经不能满足空中交通流量增长的需求。为此,本论文将尾流中对飞行安全影响最大的尾涡进行深入研究,为缩小尾流间隔提供理论基础。本论文主要通过流体力学研究方法中最经济快捷高效的数值模拟方法,利用ANSYS软件中流体力学分析模块,对尾涡流场的形成机理进行研究,以揭示近场尾涡流场特性。首先用涡粘模型中S-A模型、k-ωSST模型和Realizable k-ε模型,分别对NACA0012二维翼型在不同马赫数、不同迎角下的扰流以及NACA0012三维平直翼型的尾涡流场进行数值模拟计算,并将预测结果与风洞实验结果进行对比,分析三种数值模拟方法的优劣和模拟尾涡流场的准确性,揭示尾涡流场的形成机理。最后对有无翼尖涡扩散器的简易民航后掠翼模型分别进行数值模拟计算,进而对比分析翼尖涡扩散器对尾涡的影响。经过表面静压系数分布、升力系数曲线、极曲线、涡量、涡粘性、流线以及流场图的比较分析,得出结论:Realizable k-ε模型在数值模拟尾涡流场方面效果最佳;翼尖涡扩散器在改善翼尖处的升力分布的同时,通过分流流经翼尖的气流,将翼尖涡打散成方向不同的四个涡,以此减弱尾涡强度和尾流范围。
[Abstract]:With the continuous development of aviation industry, the existing wake safety interval is too large to meet the increasing demand of air traffic flow.Therefore, the wake vortex, which has the greatest influence on flight safety, is studied in this paper, which provides a theoretical basis for reducing the wake interval.In this paper, the formation mechanism of tail-vortex field is studied by using the most economical, fast and efficient numerical simulation method of hydrodynamic research method and the hydrodynamic analysis module in ANSYS software to reveal the characteristics of near-field tail-vortex field.Firstly, the S-A model and Realizable k- 蔚 model are used to simulate the turbulence field of NACA0012 two-dimensional airfoil at different Mach numbers and angles of attack, respectively, and the eddy-current field of NACA0012 three-dimensional flat-straight airfoil is simulated by using S-A model and Realizable k- 蔚 model respectively.By comparing the predicted results with the experimental results of wind tunnel, the advantages and disadvantages of the three numerical simulation methods and the accuracy of simulating the tail-vortex field are analyzed, and the formation mechanism of the tail-eddy current field is revealed.Finally, the airfoil vortex diffuser is numerically simulated, and the influence of the wingtip vortex diffuser on the wake vortex is compared and analyzed.Through the comparison and analysis of surface static pressure coefficient distribution, lift coefficient curve, polar curve, vorticity, eddy viscosity, streamline and flow field diagram, it is concluded that: realizable k- 蔚 model has the best effect in numerical simulation of tail vortex field.The tip vortex diffuser not only improves the lift distribution at the airfoil tip, but also disperses the wingtip vortex into four vortices in different directions by diverting the airflow through the airfoil tip, so as to weaken the wake intensity and wake range.
【学位授予单位】：中国民航大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V211.4

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