期刊文献+

翼型参数对旋翼悬停气动噪声特性影响 被引量:1

Effects of airfoil parameters on hover rotor aerodynamic acoustic performance
下载PDF
导出
摘要 基于运动嵌套网格的欧拉方程建立了旋翼流场的数值模拟方法。以旋翼气动性能仿真结果作为输入,应用FARASSATE1A公式发展了适用于旋翼气动噪声的计算程序。通过与C-T旋翼的实验数据对比,验证了方法的有效性。在此基础上,通过改变旋翼桨叶翼型的厚度、弯度以及最大弯度位置研究了翼型参数对旋翼悬停气动噪声特性的影响。研究结果表明,翼型厚度是决定旋翼厚度噪声的关键因素,旋翼载荷噪声决定于旋翼桨叶表面压力分布。旋翼厚度噪声主要受翼型厚度变化影响,旋翼载荷噪声则主要受翼型最大弯度和最大弯度位置的影响。翼型参数变化不会明显改变旋翼气动噪声的方向特性。 A numerical simulation of rotor flow-field was proposed based on the unsteady Euler equations with moving chimera grid. Calculation procedure predicting helicopter rotor aerodynamic and noise was developed using the formula of FARASSATE1 A and making simulation results of rotor aerodynamic performance as an input. A comparison against the experimental data of C-T rotor verified the availability of the simulation. The effects of airfoil parameters on rotor acoustics were analyzed by changing airfoil thickness,camber,and max camber position. The results showthat airfoil thickness is a crucial influence factor for rotor thickness noise. The loading noise highly depends on the pressure distribution of blade surface,associated with biggest bending of airfoil and its position. The airfoil parameters of rotor blade do not remarkably change the directivity of thickness and loading noise.
出处 《沈阳航空航天大学学报》 2016年第4期1-8,共8页 Journal of Shenyang Aerospace University
基金 国家自然科学基金(项目编号:51307004)
关键词 翼型参数 旋翼流场 旋翼气动 旋翼噪声 方向特性 airfoil parameter rotor flow-field rotor aerodynamic rotor acoustic directivity
  • 相关文献

参考文献28

  • 1BRENTNER K S. Prediction of helicopter rotor dis- crete frequency noise-a computer program incorpora- ting realistic motions and advanced acoustic formula- tion[ C]. NASA-TM-87721,1986.
  • 2RICHARD SICKENBERGER. Modeling helicopter near-horizon harmonic noise due to transient maneu- vers [ D ]. Maryland: University of Maryland College Park,2012.
  • 3ALLEN C B. An unsteady multiblock multigrid scheme for lifting forward flight rotor simulation [ J ] International Journal for Numerical Methods in Flu- ids, 2004,45 ( 9 ) : 973 - 984.
  • 4YU Y H, TUNG C, van der Wall B, et al. The HART-II test: Rotor Wakes and Aeroacoustics with Higher- Harmonic Pitch Control (HHC) Inputs[ C ]. Proceed- ings of the AHS 58th Annual Forum,2002.
  • 5JACKLIN S A,BLAAS A,TEVES D,et al. Reduction of helicopter bvi noise, vibration, and power consump- tion through individual blade control [ C ]. Proceedings of the AHS 51 st AnnualForum, 1995.
  • 6SIM B. WC. Suppressing in-plane, low-frequency heli- copter harmonic noise with active controls [ C ]. Amer- ican Helicopter Society Technical Specialists' Confer- ence, San Francisco: CA,2008.
  • 7SARGENT D C. Active jet acoustic control of low fre- quency in-plane helicopter harmonic noise[ D]. Mary- land :University of Maryland College Park,2012.
  • 8DESOPPER A, LAFON P, PHILIPPE J J, et al. Effect of an anhedral sweptback tip on the performance of a helicopter rotor[ JJ. Vertica, 1988,12 (4) :345 - 355.
  • 9尹建平.直升机噪声及其控制技术的研究[D].南京:南京航空航天大学,1996.
  • 10蔡伟,王阳,招启军.应用非均布桨叶设计方法的旋翼降噪技术研究[J].直升机技术,2008(3):86-91. 被引量:4

二级参考文献33

  • 1段广战,陈平剑.直升机旋翼厚度噪声研究[J].直升机技术,2007(1):6-10. 被引量:5
  • 2陈平剑,徐玉貌.旋翼桨叶气动外形设计[J].直升机技术,2007(3):16-19. 被引量:4
  • 3王立群.直升机旋翼流场Euler方程计算与噪声预测[M].西北工业大学,1998..
  • 4[1]Sternfeld H.Jr.,Advanced Rotoreraft Noise,In:American Institute of Aeronautics and Astronautics,International Meeting and Technical Display on Global Technology 2000,Baltimore,United States,May 1980.
  • 5[3]Riley R.G.,Effects of uneven blade spacing on ducted tail rotor acoustics.presented at the American Helicopter Society 52nd Annual Forum,Washington D C,1996.
  • 6[4]Brentner K.S.,Edwards B.,et al.Predicted Noise for a Main Rotor with Modulated Blade Spacing.presented at the American Helicopter Society 58th Annual Forum,Montréal,Canada,2002.
  • 7[6]Shahady P.A.,Lyon C.A.,Sehauer J.J.,Chopin M.H.,Ewing M.S.,The Effects of Modulated Blade Spacing on Static Rotor Acoustics and Performance.American Institu-te of Aeronautics and Astronautics,Aero-Acoustics Con-ference,Seattle,United States,1973.
  • 8[7]Ewald D.,Pavlovic A.,BoUinger J.G.,Noise Reduction by Applying Modulation Principles.The Journal of Acous-tieal Society of America,Vol.49,No.5,1971.
  • 9[8]Sullivan B.M.,Edwards B.D.,et al,A Subjective Test of Modulated Blade Spacing for Helicopter Main Rotors,presented at the American Helicopter Society 58th Annual Forum,Montr al,Canada,2002.
  • 10[9]Vialle M.,Amaud G.,A New Generation of Fenestron Fan-in-fin Tail Rotor on EC-135.presented at the 19th European Rotoreraft Society Forum,Moscow,1993.

共引文献36

同被引文献37

引证文献1

二级引证文献2

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