摘要
针对超临界翼型的流动特征,利用计算流体力学方法,通过典型算例开展了对多鼓包技术流动机理与减阻特性的研究。首先对超临界翼型的绕流特征进行了分析,在流动发生转捩的前缘区域布置鼓包,改善翼型前段的压力梯度,减小湍流粘性,达到减阻的目的。然后在典型超临界翼型RAE2822上,研究了前缘鼓包与激波鼓包分别单独作用时,其几何外形和位置参数对减阻的影响。最后对前缘鼓包、激波鼓包的位置和形状参数进行了协同调整,研究了前缘鼓包对常用激波鼓包的减阻效果的影响。经计算,前后鼓包共同减阻的效果确实优于单独激波鼓包,最大减阻量可达11.5%。
We study the flow characteristics of supercritical airfoil;we have tested some classic examples the flow mechanism of multi-bump technology and to study the characteristics of drag reduction by taking to explore advantage of Computational Fluid Dynamics （CFD） method. We analyze the flow mechanism of muhi-bump and then adjust the location and the geometry of multi-block. We find that not only the bump near the shock can reduce the wave drag but also the bump located near the leading-edge can improve the flow properties of airfoil. We applied multi- bump technology to RAE2822, and we find that the multi-bump technology can get more drag reduction, and that the total drag reduction can reach 11.5%.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2013年第4期517-521,共5页
Journal of Northwestern Polytechnical University
关键词
飞行器
翼型
CFD
减阻
升阻比
压力分布
流动机制
多鼓包
aircraft, airfoils, computational fluid dynamics, drag reduction, lift darg ratio, pressure distribution,schematic diagrams
flow mechanism, multi-bump
