翼型动态失速的变下垂前缘控制数值模拟

黄勇; 牟斌; 陈作斌; 刘刚

翼型动态失速的变下垂前缘控制数值模拟

中国空气动力研究与发展中心计算空气动力研究所, 绵阳 621000

基金项目: 西北工业大学翼型、叶栅空气动力学实验室基金(51462010305KG2901)

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- 被引次数: 0
出版历程
- 收稿日期: 2007-03-19
- 修回日期: 2007-06-15
- 刊出日期: 2008-03-28

Numerical investigation of dynamic stall control using variable droop leading edge airfoil

Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

摘要

摘要: 用CFD方法对VR-12翼型可压缩动态失速的变下垂前缘控制概念进行了数值模拟研究.模拟结果显示,变下垂前缘控制能在最大升力下降不大的情况下,非常显著地降低最大阻力,减小俯仰力矩负峰值,明显改善动态失速的负面效应.在流动机理上,变下垂前缘控制完全消除了动态失速涡.对参数影响的模拟研究表明,变下垂前缘控制的优势对马赫数、简缩频率或下垂控制方式的变化不敏感,是一种健壮的翼型可压缩动态失速控制手段.
- 航空、航天推进系统 /
- 翼型 /
- 动态失速 /
- 流动控制 /
- 数值模拟
Abstract: Numerical simulation for the variable droop leading-edge(VDLE) concept proposed to control the compressible dynamic stall of the VR-12 airfoil was presented. Computational results validate that VDLEcan decrease considerably the maximum drag and improve the minimum pitching moment simultaneously while the lift is maintained almost at the same high level.The reason for VDLEhaving achieved these benefits,from the perspective of flow mechanism,is its ability to eliminate completely the dynamic stall vortex occurred on the baseline.Investigation of the effects of parameters shows that the control benefits of VDLEare not sensitive to the variation of Mach number,reduced frequency or drooping control methods,which implies that the VDLEis a robust control method for the compressible dynamic stall of airfoil.
- aerospace propulsion system /
- airfoil /
- dynamic stall /
- flow control /
- numerical simulation

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参考文献(8)

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