| 翼型动态失速的变下垂前缘控制数值模拟 |
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| 引用本文： | 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[J].航空动力学报,2008,23(3):496-504. |
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| 作者姓名： | 黄勇 牟斌 陈作斌 刘刚 |
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| 作者单位： | 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 |
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| 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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| 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.
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| 关 键 词： | 航空、航天推进系统 翼型 动态失速 流动控制 数值模拟 |
| 文章编号： | 1000-8055(2008)03-0496-09 |
| 收稿时间： | 2007/3/19 0:00:00 |
| 修稿时间： | 2007年3月19日 |
Numerical investigation of dynamic stall control using variable droop leading edge airfoil |
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| HUANG Yong,MOU Bin,CHEN Zuo-bin and LIU Gang.Numerical investigation of dynamic stall control using variable droop leading edge airfoil[J].Journal of Aerospace Power,2008,23(3):496-504. |
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| Authors: | HUANG Yong MOU Bin CHEN Zuo-bin and LIU Gang |
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| Institution: | Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China;Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China;Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China;Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China |
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| 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 VDLE can 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 VDLE having 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 VDLE are not sensitive to the variation of Mach number,reduced frequency or drooping control methods,which implies that the VDLE is a robust control method for the compressible dynamic stall of airfoil. |
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| Keywords: | aerospace propulsion system airfoil dynamic stall flow control numerical simulation |
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