AI Chat Paper
Note: Please note that the following content is generated by AMiner AI. SciOpen does not take any responsibility related to this content.
{{lang === 'zh_CN' ? '文章概述' : 'Summary'}}
{{lang === 'en_US' ? '中' : 'Eng'}}
Chat more with AI
Powered by AMiner. Clicking this button will take you away from SciOpen.
Home Chinese Journal of Aeronautics Article
Article Link
Cite
EndNote(RIS) BibTeX
Collect
Show Outline
Outline
Show full outline
Hide outline
Outline
Show full outline
Hide outline
Full Length Article | Open Access

A novel hybrid method for aerodynamic noise prediction of high-lift devices

Jun TAOa,b, Gang SUNa( )
Department of Aeronautics & Astronautics, Fudan University, Shanghai 200433, China
Key Laboratory of Aerodynamic Noise Control, China Aerodynamics Research and Development Center, Mianyang 621000, China
Show Author Information

Abstract

Aerodynamic noise of High-Lift Devices (HLDs) is one of the main sources of airframe noise, and has immediate impacts on the airworthiness certification, environmental protection and security of commercial aircraft. In this study, a novel hybrid method is proposed for the aerodynamic noise prediction of HLD. A negative Spalart-Allmaras (S-A) turbulence model based Improved Delayed Detached Eddy Simulation (IDDES) method coupling with AFT-2017b transition model is developed, in order to elaborately simulate the complex flow field around the HLD and thus obtain the information of acoustic sources. A Farassat-Kirchhoff hybrid method is developed to filter the spurious noise sources caused by the vortex motions in solving the Ffowcs Williams-Hawkings (FW-H) equation with permeable integral surfaces, and accurately predict the far-field noise radiation of the HLD. The results of the 30P30N HLD indicate that, the computational Sound Pressure Levels (SPLs) obtained by the Farassat-Kirchhoff hybrid method conform well with the experimental ones in the spectrum for the given observation point, and are more accurate than those obtained by the Farassat 1A method. Based on the hybrid method, the acoustic directivity of the HLD of a commercial aircraft is obtained, and the variation of the SPLs in the spectrum with the deflection angle of the slat is analyzed.

Keywords

IDDESAerodynamic noiseFarassat-Kirchhoff hybrid methodHigh-lift devicesNegative S-A turbulence model

References

1

Khorrami MR, Singer BA, Berkman ME. Time-accurate simulations and acoustic analysis of slat free shear layer. AIAA J 2002;40(7): 1284-91.
Crossref Google Scholar
2
Khorrami M, Choudhari M, Jenkins L. Characterization of unsteady flow structures near leading-edge slat: Part II: 2D computations. Reston: AIAA; 2004. Report No.: AIAA-2004-2802.
Crossref
3

Choudhari MM, Khorrami MR. Effect of three-dimensional shear-layer structures on slat cove unsteadiness. AIAA J 2007;45(9):2174-86.
Crossref Google Scholar
4
Lockard D, Choudhari M. Noise radiation from a leading-edge slat. Reston: AIAA; 2009. Report No.: AIAA-2009-3101.
Crossref
5

Zhang YF, Chen HX, Wang K, et al. Aeroacoustic prediction of a multi-element airfoil using wall-modeled large-eddy simulation. AIAA J 2017;55(12):4219-33.
Crossref Google Scholar
6

Huang H, Li WP, Wang FX. Slat noise suppression with mass injection. J Aircr 2014;52(1):31-41.
Crossref Google Scholar
7
Nebenführ B, Peng SH, Davidson L. Hybrid RANS-LES simulation of turbulent high-lift flow in relation to noise generation. In: Progress in hybrid RANS-LES modelling. Berlin: Springer; 2012. p. 303-14.
Crossref
8
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. Reston: AIAA; 2015. Report No.: AIAA-2015-3132.
Crossref
9
Sakai R, Ishida T, Murayama M, et al. Effect of subgrid length scale in DDES on aeroacoustic simulation around three-element airfoil. Reston: AIAA; 2018. Report No.: AIAA-2018-0756.
Crossref
10
Ashton N, West A, Mendonca F. Slat noise prediction using hybrid RANS-LES methods on structured and unstructured grids. Reston: AIAA; 2015. Report No.: AIAA-2015-3139.
Crossref
11
Kozubskaya T, Abalakin I, Duben A, et al. Numerical simulation of slat noise of high-lift devices using immersed boundary method on unstructured meshes. Reston: AIAA; 2019. Report No.: AIAA-2019-2461.
Crossref
12

Ewert R, Schröder W. On the simulation of trailing edge noise with a hybrid LES/APE method. J Sound Vib 2004;270(3):509-24.
Crossref Google Scholar
13
Ewert R, Emunds R. CAA slat noise studies applying stochastic sound sources based on solenoidal digital filters. Reston: AIAA; 2005. Report No.: AIAA-2005-2862.
Crossref
14

Ewert R. Broadband slat noise prediction based on CAA and stochastic sound sources from a fast random particle-mesh (RPM) method. Comput Fluids 2008;37(4):369-87.
Crossref Google Scholar
15
Ewert R, Dierke J, Appel C, et al. CAA-RPM prediction and validation of slat setting influence on broadband high-lift noise generation. Reston: AIAA; 2010. Report No.: AIAA-2010-3833.
Crossref
16
Dierke J, Ewert R, Chappuis J, et al. The influence of realistic 3-D viscous mean flow on shielding of engine-fan noise by a 3-element high-lift wing. Reston: AIAA; 2010. Report No.: AIAA-2010-3917.
Crossref
17

Zhang X. Airframe noise: High lift device noise. Encyclopedia Aerospace Eng 2008;6:3541-51.
Google Scholar
18

Zhang X. Aircraft noise and its nearfield propagation computations. Acta Mechanica Sinica 2012;28(4):960-77.
Crossref Google Scholar
19

Wang X, Hu ZW, Zhang X. Aeroacoustic effects of high-lift wing slat track and cut-out system. Int J Aeroacoustics 2013;12(3):283-307.
Crossref Google Scholar
20

Liu X, Lu H, Huang W. Numerical simulation of aeroacoustics based on higher order DG method. Aeronautical Comput Technique 2012;42(6):21-24, [Chinese].
Google Scholar
21
Bai BH, Li XD, Guo YP, et al. Prediction of slat broadband noise with RANS results. Reston: AIAA; 2015. Report No.: AIAA-2015-2671.
Crossref
22

Bai B, Li X. A RANS-based prediction method for the airfoil broadband trailing edge noise. J Aerospace Power 2016;31(1):115-123, [Chinese].
Google Scholar
23
Gao JH, Li XD, Lin DK. Numerical simulation of the noise from the 30P30N highlift airfoil with spectral difference method. Reston: AIAA; 2017. Report No.: AIAA-2017-3363.
Crossref
24
König D, Schröder W, Meinke M. Numerical analysis of sound generating mechanisms of a high-lift device. In: Notes on numerical fluid mechanics and multidisciplinary design (NNFM). Berlin: Springer; 2007. p. 421–9.
Crossref
25
Kanjere K, Zhang X, Hu ZW, et al. Aeroacoustic investigation of deployed spoiler during steep approach landing. Reston: AIAA; 2010. Report No.: AIAA-2010-3992.
Crossref
26

Ma ZK, Zhang X. Numerical investigation of broadband slat noise attenuation with acoustic liner treatment. AIAA J 2009;47(12):2812-20.
Crossref Google Scholar
27
Khorrami MR, Mineck RE. Towards full aircraft airframe noise prediction: detached eddy simulations. Reston: AIAA; 2014. Report No.: AIAA-2014-2480.
Crossref
28

Salas P, Moreau S. Aeroacoustic simulations of a simplified high-lift device accounting for some installation effects. AIAA J 2016;55(3):774-89.
Crossref Google Scholar
29

Wang HJ, Tian JY, Luo W. Three-dimensional simulation analysis of the influence of slat structural parameters on slat aerodynamic noise. Journal Northwest Polytech Univ 2019;37(6):1129-1137 [Chinese].
Crossref Google Scholar
30

Wang M, Lele SK, Moin P. Computation of quadrupole noise using acoustic analogy. AIAA J 1996;34(11):2247-54.
Crossref Google Scholar
31
Zhong SY, Zhang X. A sound extrapolation method for aeroacoustics far-field prediction in presence of vortical waves. J Fluid Mech 2017;820: 424–50.
Crossref
32

Zhong SY, Zhang X. A sound extrapolation method for aeroacoustics far-field prediction in presence of vortical waves. J Fluid Mech 2017;820:424-50.
Crossref Google Scholar
33

Mao YJ, Hu ZW. Analysis of spurious sound due to vortical flow through permeable surfaces. Aerosp Sci Technol 2020;96: 105544.
Crossref Google Scholar
34

Nordanger K, Holdahl R, Kvamsdal T, et al. Simulation of airflow past a 2D NACA0015 airfoil using an isogeometric incompressible Navier-Stokes solver with the Spalart-Allmaras turbulence model. Comput Methods Appl Mech Eng 2015;290:183-208.
Crossref Google Scholar
35
Stefanski DL, Glasby RS, Erwin JT, et al. Improvements to the amplification factor transport transition model for finite-element implementations. Reston: AIAA; 2019. Report No.: AIAA-2019-0040.
Crossref
36

Chen SS, Cai FJ, Xiang XH, et al. A low-diffusion robust flux splitting scheme towards wide-ranging Mach number flows. Chin J Aeronaut 2021;34(5):628-41.
Crossref Google Scholar
37

Han SQ, Song WP, Han ZH. A novel high-order scheme for numerical simulation of wake flow over helicopter rotors in hover. Chin J Aeronaut 2022;35(5):260-74.
Crossref Google Scholar
38

Zhou D, Lu ZL, Guo TQ, et al. Aeroelastic prediction and analysis for a transonic fan rotor with the “hot” blade shape. Chin J Aeronaut 2021;34(7):50-61.
Crossref Google Scholar
39

Xiao TH, Zhi HL, Deng SH, et al. Enhancement on parallel unstructured overset grid method for complex aerospace engineering applications. Chin J Aeronaut 2023;36(1):115-38.
Crossref Google Scholar
40
Harris CD. Two-dimensional aerodynamic characteristics of the NACA0012 airfoil in the Langley 8 foot transonic pressure tunnel. Washington, D.C.: NASA; 1981. Report No.: NASA-TM-81927.
41
Ladson CL. Effects of independent variation of Mach and Reynolds numbers on the low-speed aerodynamic characteristics of the NACA0012 airfoil section. Washington, D.C.: NASA, 1988. Report No.: 19880019495.
42
Somers D. Design and experimental results for a flapped natural-laminar-flow airfoil for general aviation applications. Washington, D.C.: NASA, 1981. Report No.: NASA TP-1861.
43

Tao J, Sun G. An artificial neural network approach for aerodynamic performance retention in airframe noise reduction design of a 3D swept wing model. Chin J Aeronaut 2016;29(5):1213-25.
Crossref Google Scholar
44
Lopes L, Boyd DD, Nark D, et al. Identification of spurious signals from permeable ffowcs williams and hawkings surfaces. Washington, D.C.: NASA, 2017. Report No.: 20170005478.
45

Shur ML, Spalart PR, Strelets MK. Noise prediction for increasingly complex jets. Part I: Methods and tests. Int J Aeroacoustics 2005;4(3):213-45.
Crossref Google Scholar
46

Spalart PR, Shur ML, Strelets MK, et al. Initial noise predictions for rudimentary landing gear. J Sound Vib 2011;330(17):4180-95.
Crossref Google Scholar
47

Spalart PR, Shur ML. Variants of the ffowcs williams - hawkings equation and their coupling with simulations of hot jets. Int J Aeroacoustics 2009;8(5):477-91.
Crossref Google Scholar
48

Wright MCM, Morfey CL. On the extrapolation of acoustic waves from flow simulations with vortical out flow. Int J Aeroacoustics 2015;14(1–2):217-27.
Crossref Google Scholar
49

Zhong SY, Zhang X. On the frequency domain formulation of the generalized sound extrapolation method. J Acoust Soc Am 2018;144(1):24.
Crossref Google Scholar
50

Zhong SY, Zhang X. A generalized sound extrapolation method for turbulent flows. Proc R Soc A 2018;474(2210):20170614.
Crossref Google Scholar
51

Wang XL, Wang FX, Li YL. Aerodynamic characteristics of high-lift devices with downward deflection of spoiler. J Aircr 2011;48(2):730-5.
Crossref Google Scholar
52
Pascioni KA, Cattafesta LN. Aeroacoustic measurements of leading-edge slat noise. Reston: AIAA; 2016. Report No.: AIAA-2016-2960.
Crossref
53
Wang XL, Wang FX, Li YL. Aerodynamic characteristics of high-lift devices with downward deflection of spoiler. J Aircr 2011;48(2): 730–5.
Crossref
Chinese Journal of Aeronautics
Volume 36 Issue 9,
September 2023
Pages 151-161
DOI: 10.1016/j.cja.2023.06.027
Cite this article:
TAO J, SUN G. A novel hybrid method for aerodynamic noise prediction of high-lift devices. Chinese Journal of Aeronautics, 2023, 36(9): 151-161. https://doi.org/10.1016/j.cja.2023.06.027

55

Views

2

Crossref

1

Web of Science

3

Scopus

Altmetrics
Received: 28 August 2022
Revised: 19 October 2022
Accepted: 28 November 2022
Published: 28 June 2023
© 2023 Chinese Society of Aeronautics and Astronautics.

This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).
Return