三段翼型气动噪声特性数值分析

薛丝丹; 何嘉华; 刘秋洪; 蔡晋生

doi:10.7638/kqdlxxb-2021.0134

欢迎来到能源电力期刊网！

English Version 期刊登录

您当前的位置：

首页 >

文章列表页 >

三段翼型气动噪声特性数值分析

研究论文 | 更新时间：2026-05-28

- 三段翼型气动噪声特性数值分析
- Numerical analysis of the aerodynamic noise characteristics of a three-element airfoil
- 空气动力学学报 2022年40卷第6期页码：92-101
- 作者机构：
  
  西北工业大学翼型叶栅空气动力学重点实验室,西安,710072
- 作者简介：
  
  薛丝丹（2000-），女，本科生，陕西渭南人，研究方向：气动声学. E-mail：xuesidan@mail.nwpu.edu.cn
  刘秋洪*（1977-），男，博士，副教授，湖南株洲人，研究方向：空气动力学，气动声学. E-mail：qhliu@nwpu.edu.cn
- 基金信息：
  
  翼型、叶栅空气动力学重点实验室基金（JZX7Y202001SY002101-614220120030101）;航空科学基金（201914053001）;气动噪声控制重点实验室开放课题（ANCL20200303）
- DOI：10.7638/kqdlxxb-2021.0134
  中图分类号： V211.3
- 纸质出版：2022
- 稿件说明：
移动端阅览
薛丝丹, 何嘉华, 刘秋洪, 等. 三段翼型气动噪声特性数值分析[J]. 空气动力学学报, 2022, 40(6): 92−101.

XUE Sidan, HE Jiahua, LIU Qiuhong, et al. Numerical analysis of the aerodynamic noise characteristics of a three-element airfoil[J]. 2022, 40(6): 92-101.
薛丝丹, 何嘉华, 刘秋洪, 等. 三段翼型气动噪声特性数值分析[J]. 空气动力学学报, 2022, 40(6): 92−101. DOI： 10.7638/kqdlxxb-2021.0134

XUE Sidan, HE Jiahua, LIU Qiuhong, et al. Numerical analysis of the aerodynamic noise characteristics of a three-element airfoil[J]. 2022, 40(6): 92-101. DOI： 10.7638/kqdlxxb-2021.0134.

摘要

采用混合计算气动声学方法对某三段翼气动噪声特性进行分析，气动声源采用IDDES方法模拟，噪声传播预估采用Curle方程。利用圆柱-NACA0012翼型绕流算例对数值算法进行验证，近场气动声源与远场气动噪声的预测结果和实验相吻合，IDDES方法可以精细捕捉涡脱落、分离和再附着等非定常流动现象，能为气动噪声的预测提供足够精确的声源信息；采用Curle方程能够准确高效地预测远场气动噪声，对低马赫数流动可以忽略四极子声源对远场的贡献。在此基础上，对来流迎角7.5°、马赫数0.17和雷诺数1.71×10

的某三段翼气动特性和噪声特性进行预测，结果表明：襟翼表面脉动压力对噪声贡献最大，缝翼表面脉动压力对噪声贡献最小；1000 Hz附近的低频噪声源于襟翼尾缘剪切层流动分离和尾涡脱落；缝翼凹腔内的涡脱落、融合和撞击主要诱发500 Hz以下的低频噪声；襟翼尾涡脱落和主翼后缘下方流动分离则产生4500 Hz附近中频噪声。

Abstract

A hybrid computational aeroacoustics technique was performed to investigate the aerodynamic noise characteristics of a three-element airfoil. The aerodynamic source was simulated with an improved delayed detached eddy simulation (IDDES) method and the far-field aerodynamic noise was computed by Curle's equation. The noise generated by a low Mach number flow past the rod-airfoil configuration was evaluated by the numerical approach and compared with the experimental data. The comparison shows that IDDES method can accurately describe the flow characteristics including the vortex shedding

detachment

and reattachment

and provide detailed sources for the prediction of the acoustic far-field. The Curle's equation can evaluate the far-field noise accurately and efficiently. The quadrupole source can be neglected for the acoustic far-field of a low Mach number flow. Therefore

the aeroacoustics and aerodynamics characteristics of the three-element airfoil at Reynolds number of 1.71×10

Mach number 0.17 and angle of attack 7.5° were analyzed. The pressure fluctuation on the surface of the flap exerts largest influence on the acoustic far-field while the slat exerts minimum. The peak values of the noise near 1000 Hz are generated by the shear layer flow separation and the vortex shedding at the trailing edge of the flap. The vortex shedding

fusion and collision in the slat cove mainly induce noise below 500 Hz. The noises near 4500 Hz are resulted from the vortex shedding at the trailing edge of the flap and the flow separation at the trailing edge of the main wing suction surface.

关键词

Keywords

references

LIU P Q, LI L, XING Y, et al. Developments of aeroacoustic investigation on high-lift device for large aircrafts[J]. Acta Aerodynamica Sinica, 2017, 35(4): 472-484. (in Chinese)

FFOWCS WILLIAMS J E, HAWKING D L. Sound generation by turbulence and surfaces in arbitrary motion [J]. Philosophical Transactions of the Royal Society, 1969, A264: 321-342.

MAO Y J. Development of acoustic analogy for low Mach numbers flow and its applications [D]. Xi’an, Xi`an Jiaotong University, 2010 (in Chinese).

PIOMELLI U. Large-eddy simulation: achievements and challenges[J]. Progress in Aerospace Sciences, 1999, 35(4): 335-362. DOI:10.1016/S0376-0421(98)00014-1

SPALART P R, JOU W H, STRELETS M, et al. Comments on the feasibility of LES for wings and on a hybrid RANS/LES approach [M]. Proceedings of the 1st AFSOR International Conference on DNS/LES, Greyden Press, Columbus, OH, 1997: 137-147.

SPALART P R, DECK S, SHUR M L, et al. A new version of detached-eddy simulation, resistant to ambiguous grid densities[J]. Theoretical and Computational Fluid Dynamics, 2006, 20(3): 181-195. DOI:10.1007/s00162-006-0015-0

LI W P. Review of the mechanism and noise control of high-lift device noise[J]. Acta Aerodynamica Sinica, 2018, 36(3): 372-384, 409. (in Chinese)

PASCIONI K, CATTAFESTA L N, CHOUDHARI M M. An experimental investigation of the 30P30N multi-element high-lift airfoil[C]// 20th AIAA/CEAS Aeroacoustics Conference, Atlanta, GA. Reston, Virginia: AIAA, 2014. doi: 10.2514/6.2014-3062

BALAJI R, BRAMKAMP F, HESSE M, et al. Effect of flap and slat riggings on 2-D high-lift aerodynamics[J]. Journal of Aircraft, 2006, 43(5): 1259-1271. DOI:10.2514/1.19391

LI L, LIU P Q, GUO H, et al. Aerodynamic and aeroacoustic experimental investigation of 30P30N high-lift configuration[J]. Applied Acoustics, 2018, 132: 43-48. DOI:10.1016/j.apacoust.2017.11.002

FEJTEK I, FEJTEK I. Summary of code validation results for a multiple element airfoil test case[C]// 28th Fluid Dynamics Conference, Snowmass Village, CO. Reston, Virginia: AIAA, 1997 doi: 10.2514/6.1997-1932

LU Q H, CHEN B. Analysis of aeroacoustics characteristics of high lift device using LES method[J]. Acta Aerodynamica Sinica, 2016, 34(4): 448-455 (in Chinese).

ZHANG Y F, CHEN H X, WANG K, et al. Aeroacoustic prediction of a multi-element airfoil using wall-modeled large-eddy simulation[J]. AIAA Journal, 2017, 55(12): 4219-4233. DOI:10.2514/1.J055853

TERRACOL M, MANOHA E, MURAYAMA M, et al. Aeroacoustic calculations of the 30P30N high-lift airfoil using hybrid RANS/LES methods: modeling and grid resolution effects[C]// 21st AIAA/CEAS Aeroacoustics Conference, Dallas, TX. Reston, Virginia: AIAA, 2015 doi: 10.2514/6.2015-3132

CHEN Y C, LI Y L, YE J K, et al. Study progress about high-lift system of C919 airplane[J]. Advances in Aeronautical Science and Engineering, 2010, 1(1): 1-5. (in Chinese)

CURLE N. The influence of solid boundaries on aerodynamic sound [J]. Proceedings of the Royal Society of London, 1955, 213A, 1187: 505-514.

JIN Y, LIAO F, CAI J S, et al. Investigation on rod-airfoil noise with high-order cell-centered finite difference method and acoustic analogy[J]. Aerospace Science and Technology, 2020, 102: 105851. DOI:10.1016/j.ast.2020.105851

MACCORMACK R, MACCORMACK R. A new implicit algorithm for fluid flow[C]// 13th Computational Fluid Dynamics Conference, Snowmass Village, CO, USA. Reston, Virigina: AIAA, 1997. doi: 10.2514/6.1997-2100

JACOB M C, BOUDET J, CASALINO D, et al. A rod-airfoil experiment as a benchmark for broadband noise modeling[J]. Theoretical and Computational Fluid Dynamics, 2005, 19(3): 171-196.

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

基于LBM方法的LAGOON起落架噪声预测与降噪方法研究

FW-H方程在声学速度预测中的拓展

大型气动声学风洞折线型集气口段流场特性数值研究与试验验证

大型气动声学风洞轴流风扇气动与噪声特性数值评估

不同边界条件下单圆柱气动噪声大涡模拟研究