期刊文献+

基于模糊逻辑方法的风力机动态失速研究

STUDY ON WIND TURBINE DYNAMIC STALL BASED ON FUZZY LOGIC METHOD
原文传递
导出
摘要 基于模糊逻辑数学方法建立了风力机动态失速模型,用于计算风力机翼型的非定常气动载荷。以风力机翼型S809为算例进行了非定常气动载荷的计算。计算结果表明:基于模糊逻辑的动态失速模型得到的预测结果与试验数据吻合良好,且比Leishman-Beddoes模型具有更高的预估精度,能够捕捉风力机翼型动态失速的细节特征,从而证明了该方法的正确性和有效性。 Based on the fuzzy logic method, a new wind turbine dynamic-stall model is brought forward to calculate the unsteady aerodynamic loads of wind turbine airfoil. As a numerical example, the unsteady aerodynamic loads on S809 airfoil were calculated. The results show that the fuzzy logic model reconstructs the unsteady aerodynamic loads very well, and can capture the detail features of the dynamic stall of the wind turbine airfoils. Also, the comparison results show that the prediction accuracy is better than the Leishman-Beddoes model.
作者 陆洋 周桂林
出处 《太阳能学报》 EI CAS CSCD 北大核心 2012年第2期210-214,共5页 Acta Energiae Solaris Sinica
关键词 风力机 模糊逻辑 动态失速 非定常气动载荷 wind turbine fuzzy logic theory dynamic stall unsteady aerodynamic loads
  • 相关文献

参考文献12

  • 1Gormont R E. A mathematical model of unsteady aerody- namics and radial flow for application to helicopter rotors [ R]. USA AVLABS Technical Report, 1970.
  • 2Petot D. Progress in the semi-empirical prediction of the aerodynamic forces due to large amplitude oscillations of an airfoil in attached or separated flow [ R ]. Eur Rotor- craft Forum, 1983.
  • 3Lin G F, Lan C E. A generalized dynamic aerodynamic coefficient model for flight dynamic application[R]. AIAA 97-3643, 1997.
  • 4Leishman J G, Beddoes T S. A semi-empirical model for dynamic stall[ J]. Journal of the American Helicopter So- ciety, 1989, 34(3): 3-17.
  • 5Sheng W, Galbraith R A, Coton F N. Improved dynamic- stall-onset criterion at low roach numbers [ J ]. Journal of Aircraft, 2007, 44 (3) : 1049-1052.
  • 6Gutpa S, Leishman J G. Dynamic stall modeling of the S809 airfoil and comparison with experiments[ R]. AIAA- 06-0196, 2006.
  • 7Sheng W , Galbraith R A McD, Coton F N. A new stall onset criterion for low speed dynamic stall [ J ]. Journal of Solar Energy Engineering, 2006, 128(4) : 461-471.
  • 8Hu C C, Lan C E. Unsteady aerodynamic models for ma- neuvering aircraft[R]. AIAA-93-3626-CP, 1993.
  • 9黄达,吴根兴.飞机偏航-滚转耦合运动非定常空气动力实验[J].南京航空航天大学学报,2005,37(4):408-411. 被引量:17
  • 10Zhongjun W, Edward C. Fuzzy logic modeling of nonlin- ear unsteady aerodynamics[ R]. AIAA-98-4351, 1998.

二级参考文献7

  • 1Zbigniew D,Grzegoz K,Krzysziof S. Method of control of a straked wing aircraft for cobra maneuvers[R]. ICA8-96-3.7.4, 1996.
  • 2Soltani M R. Experimental measurements on an oscillating 70-degree delta wing in subsonic flow[R].AIAA-88-2576, 1988.
  • 3Jarrah M A, Low speed wind tunnel investigation of flow about delta wings, oscillating in pitch to very high angle of attack[R]. AIAA-89-0295, 1989.
  • 4Brandon J M ,Shah G H. Unsteady aerodynamic characteristics of fighter model undergoing large-amplirude pitching motions at high angles of attack[R].AIAA-90-0309, 1990.
  • 5Hanff E S, Jenkins S B. Large-amplitude high-rate roll experiments on a delta and double delta wing[R]. AIAA-90-0224, 1990.
  • 6Michael C, Francis S. X-31 enhanced fighter maneuverability demonstrator:flight test achievements[R]. ICAS-94-7.2.2, 1994.
  • 7Zhongjun W,Edward C L. Unsteady aerodynamic effects on the flight characteristics of an F-16xl configuration[R]. AIAA-2000-39, 2000.

共引文献16

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部