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关节式准柔性后缘翼型的气动特性分析 被引量：2

Aerodynamic characteristics of multi-sectional variable trailing-edge airfoil
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摘要 采用面元法研究了翼面压力分布和关节数量之间的关系,同时也研究了后缘偏角、俯仰力矩系数和转轴力矩随着后缘关节数量的变化规律.计算结果表明:后缘的关节数越多,相对偏转角越小,翼型表面曲率的突变程度越低,相应表面的压力趋于平缓;但多关节式后缘无法克服柔性后缘带来的俯仰力矩偏大的问题,而且转轴力矩随着关节数的增加而逐渐增大。 The relationship between the surface pressure distribution and the number of joints was investigated by use of panel method.Effects of the number of joints on flap angle,pitching moment coefficient and shaft torque were also discussed.Results show that the relative flap angle will decrease with the increasing number of joints of trailing-edge and the wing surface and pressure distribution tend to be smooth.But the problem that the flexible trailing-edge will cause larger pitching moment can not be overcome by multi-sectional trailingedge.The shaft torque will increase with the increasing number of joints.Relevant research results can provide technical support for flexible trailing-edge designing.
作者 尹维龙
机构地区 哈尔滨工业大学复合材料与结构研究所 哈尔滨工业大学力学博士后流动站
出处 《哈尔滨工业大学学报》 EI CAS CSCD 北大核心 2010年第11期1758-1761,共4页 Journal of Harbin Institute of Technology
基金 中国博士后科学基金资助项目(20080440888)
关键词 柔性后缘 多关节 翼面压力 气动特性 转轴力矩 flexible trailing-edge multi-section surface pressure aerodynamic characteristic shaft torque
分类号 V215.3 [航空宇航科学与技术—航空宇航推进理论与工程]
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参考文献11

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共引文献22

同被引文献21

  • 1NGUYENN, PRECUP N, URNESJ, SR, eta[. F:xperi mental investigation of a flexible wing with a variable cam her continuous trailing edge flap design[C://32nd A1AA Applied Aerodynamics Conference. Reston: AIAA, 2014.
  • 2LEBOFSKY S, TING E, NGUYEN N. Aeroelastic rood eling and drag optimization of aircraft wing with wtriable camber continuous trailing edge flap:C]//32nd AIAA Ap plied Aerodynamics Conference. Reston: AIAA, 20 Id.
  • 3URNES J, SR, MORRIS C, SHEAHAN J, et a[. Con trol system design for a variable camber continuous :railil:g edge flap system on an elastic wing[ C]//55th AIAA/ ASME/ASCE/AHS/ASC Slrnctures, Structural l)yn;:m ics, and Materials Conference. Reston: AIAA, 2014.
  • 4URNES J, SR, NGUYEN N, IPPOI,I'FO C, e: a[. A mission - Adaptive variable camber flap control system Io optimize high lift and cruise lift-to drag ratios of future. Nq-3 transport aircraft[C]//51st A1AA Aerospace Sci ences Meeting Including the New Horizons Forum and Aerospace Exposition. Reston: AIAA, 2013.
  • 5SINAPIUS M, MONNER H P, KINTSCHER M, :.l :d. DLR's morphing wing activities wilIfin t}m European net work[J]. Procedia IUTAM, 2014, 10(1): d16-d26.
  • 6AHMED S, GUO S. Optima[ design and analysis of : wing with morphing high lift devices[C://54th AIAA, ASME/ASCE/AHS/ASC Structures, Structural I)ynam its, and Materials Conference. Reston: AIAA, 20101.
  • 7MATTEO N, GUO S, MORISHIMA R. Optimizalhm of leading edge and flap with actuation system for a w:rla ble camber wing [C://53rd AIAA/ASME/ASCF./AtlS ASC Structures, S:ructural Dynamics and Materials (?on ference. Reston: AIAA, 2012.
  • 8DI MATTEO N, GUO S, LI 1). Morphlng trailing :,dgcflap for high lift wing[C]//52nd AIAA/ASME/ASCE/ AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston: AIAA, 2011.
  • 9DI MATTEO N, GUO S, AHMED S, et al. Design and analysis of a morphing flap structure for high lift wingEC:// 51st AIAA/ASME/ASCE/AHS/ASC Struc- tures, Structural Dynamics, and Materials Conference. Re- ston: AIAA, 2010.
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引证文献2

二级引证文献23

哈尔滨工业大学学报
2010年 第11期

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