合成射流对钝尾缘翼型气动特性的影响

发布时间：2018-01-30 11:02

  本文关键词： 合成射流 钝尾缘翼型 数值模拟 升阻力特性 压力波动　出处：《机械工程学报》2016年04期 　论文类型：期刊论文

【摘要】：研究吸力面存在合成射流的情况下,钝尾缘翼型TR-4000-2000流场结构的变化及其升阻力系数等气动特性参数的变化趋势。在相同射流入口速度条件下,采用计算流体力学软件Fluent对相同来流速度不同攻角情况下翼型流场进行非定常数值模拟计算,分析射流前后翼型升阻力系数变化及翼型表面压力的波动状况;在此基础上,对不同射流频率和不同射流速度情况下翼型流场进行模拟计算,寻求最佳射流参数。结果表明,由于射流及尾缘涡的相互作用导致翼型的升阻力特性不断变化,钝尾缘翼型吸力面合成射流有明显的增升减阻效果,在15°攻角时尤为明显,升力系数提高约40%,阻力系数减小约25%。在量纲一射流速度和量纲一射流频率均为1时,射流对翼型的增升减阻效果最佳。
[Abstract]:It is studied that there is a synthetic jet on the suction surface. The change of TR-4000-2000 flow field structure and the variation trend of aerodynamic characteristic parameters such as lift resistance coefficient of blunt tail flange flange, under the same jet inlet velocity condition. The unsteady numerical simulation of airfoil flow field with the same incoming velocity and different attack angle was carried out by using computational fluid dynamics software Fluent. The variation of the lift resistance coefficient of the airfoil and the fluctuation of the surface pressure of the airfoil before and after the jet are analyzed. On this basis, the airfoil flow field under different jet frequency and different jet velocity is simulated and calculated to find the best jet parameters. Due to the interaction between jet and trailing edge vortex, the lift resistance of airfoil is constantly changing, and the drag and lift effect of the jet on the suction surface of blunt tail flange is obvious, especially at 15 掳angle of attack. The lift coefficient is increased by about 40 and the drag coefficient is reduced by about 25. When the velocity of dimensional-jet and the frequency of dimensional-jet are both 1:00, the effect of jet on airfoil lift and drag reduction is the best.
【作者单位】： 北京理工大学机械与车辆学院;
【基金】：高等学校博士点专项科研基金资助项目(20111101130002)
【分类号】：O358
【正文快照】： 0前言 合成射流,也即零质量射流,是一种全新的、 具有广泛应用前景的流动控制技术。与传统的流动控制手段相比,这种射流装置无机械移动部件、无需气源管道、结构紧凑,以及具有响应快、频带宽等优点,可用于分离控制、增强混合、提高微型飞机的操纵力以及实现推力矢量控制等。，

本文编号：1476081