非紧致结构气动噪声辐射散射统一积分计算方法
收稿日期: 2013-01-11
修回日期: 2013-06-13
网络出版日期: 2013-06-19
基金资助
国家自然科学基金（11002116）;西北工业大学基础研究基金（GCKY1006）
A Unified Aeroacoustic Computational Integral Method of Noise Radiation and Scattering with Noncompact Bodies
Received date: 2013-01-11
Revised date: 2013-06-13
Online published: 2013-06-19
Supported by
National Natural Science Foundation of China (11002116);Basic Research Foundation of Northwestern Polytechnical University (GCKY1006)
为避免气动噪声数值模拟中流场高精度计算所带来的巨大工作量，同时考察非紧致边界的散射效应，采用二阶精度格式进行可压缩流场计算，将流场脉动量分解为流场数值计算捕获的主要由流体运动引起的流动脉动分量和流场计算未捕获的主要由噪声传播引起的声学脉动分量两部分，基于Lighthill声模拟理论和格林函数波动方程，导出气动噪声辐射散射统一积分计算方法。首先将观察点布置在物体表面，通过统一积分方程计算得到非紧致物面边界上的散射声压，然后将观测点移到远场位置计算得到声场区域内任意观察点的声压。对二维、三维圆柱以及二维翼型开展气动噪声数值计算，结果与文献计算以及实验结果相吻合，表明本文提出的这种统一积分计算方法能够减少流场高精度计算所需的工作量，同时还能够准确地模拟非紧致结构对气动噪声的散射效应。
王芳 , 刘秋洪 , 蔡晋生 . 非紧致结构气动噪声辐射散射统一积分计算方法[J]. 航空学报, 2013 , 34(11) : 2482 -2491 . DOI: 10.7527/S1000-6893.2013.0302
In order to deal with the high requirement for computation resources of a high order method in the aeroacoustic numerical simulation, and also take into consideration the scattering effects from noncompact bodies, a unified aeroacoustic computational method of noise radiation and scattering is presented in this paper which combines the calculation of the scattering noise due to noncompact surfaces and the radiation noise induced by flow field variables. The pulsations of the flow field variables are divided into hydrodynamic components and acoustic components, and then an integral solution for scattering scattering noise and far field noise is obtained based on Lighthill acoustic analogy theory and the wave equation of Green's function. According to this method, numerical calculation is developed in two steps. The scattering pressure distribution is first obtained by solving the unified integral equation with the observation points located on the body surface, and then the far field pressure of arbitrary points is computed when the observation point is located in the far field. Verification work is developed in connection with the numerical calculation of two-dimensional and three-dimensional circular cylinders and a two-dimensional NACA0012 airfoil. The calculated aeroacoustic results agree well with experimental data and the numerical results of other methods. This shows that this unified integral method is able to calculate the scattering effect of noncompact bodies accurately while significantly reducing the computation load.
Key words： aeroacoustics; radiation; scattering; compressibility; noncompact body; integral equation
[1] Lighthill M J.On sound generated aerodynamically.I.General theory.Proceedings of the Royal Society of London,Series A: Mathematical and Physical Sciences,1952,211(1107): 564-587.
[2] Lighthill M J.On sound generated aerodynamically.Ⅱ.Turbulence as a source of sound.Proceedings of the Royal Society of London,Series A: Mathematical and Physical Sciences,1954,222(1148): 1-32.
[3] Curle N.The influence of solid boundaries on aerodynamic sound.Proceedings of the Royal Society of London,Series A: Mathematical and Physical Sciences,1952,213(1187): 505-514.
[4] Ffowcs Williams J E,Hawking D L.Sound generation by turbulence and surfaces in arbitrary motion.Philosophical Transactions of the Royal Society of London,Series A: Mathematical and Physical Sciences,1969,264(1151): 321-342.
[5] Casalino D,Jacob M.Prediction of aerodynamic sound from circular rods via spanwise statistical modelling.Journal of Sound and Vibration,2003,262(4): 815-844.
[6] Orselli R M,Meneghini J R,Saltara F.Two and three dimensional simulation of sound generated by flow around a circular cylinder.15th AIAA/CEAS Aeroacoustics Conference,2009.
[7] Revell J D,Prydz R A,Hays A P.Experimental study of airframe noise vs.drag relationship for circular cylinders.Lockheed Report 28074,Final Report NASA Contrast NASI-14403,1977.
[8] Howe M S.Edge-source acoustic Green's function for an airfoil chord,with application to trailing-edge noise.The Quarterly Journal of Mechanics and Applied Mathematics,2001,54(1): 139-155.
[9] Hu F Q,Hussaini Y H,Manthey J L.Low-dissipation and low-dispersion Runge-Kutta schemes for computational acoustics.Journal of Computational Physics,1996,124(1): 177-191.
[10] Hu F Q,Guo Y P,Jones A D.On the computation and application of exact Green's function in acoustic analogy.11th AIAA Aeroacoustics Conference,2005: 2005-2986.
[11] Jones A D,Hu F Q.A three-dimensional time-domain boundary element method for the computation of exact green's function in acoustic analogy.13th AIAA/CEAS Aeroacoustics Conference,2007.
[12] Takaishi T,Miyazawa M,Kato C.A computational method of evaluating noncompact sound based on vortex sound theory.Journal of Acoustical Society of America,2007,121(3): 1353-1361.
[13] Schram C.A boundary element extension of Curle's analogy for non-compact geometries at low-Mach numbers.Journal of Sound and Vibration,2009,322(1): 264-281.
[14] Mao Y J,Qi D T,Gu Y Y.Prediction of hydrodynamic noise scattered by the non-compact circular cylinder.ASME 3rd Joint US-European Fluids Engineering Summer Meeting,2010.
[15] Khalighi Y.Prediction of sound generated by complex flows at low Mach numbers.AIAA Journal,2010,48(2): 306-316.
[16] Morfey C L.The role of viscosity in aerodynamic sound generation.Acoustics,2003,2(3): 225-240.
[17] Cox J S,Brentner K S,Rumsey C L.Computation of vortex shedding and radiated sound for a circular cylinder: subcritical to transcritical reynolds numbers.Theoretical and Computational Fluid Dynamics,1998,12(4): 233-253.
[18] Gregory N,O'Reilly C L.Low speed aerodynamic characteristics of NACA0012 aerofoil section,including the effects of upper surface roughness simulating hoar frost.Reports and Memoranda No.3726,1973.
[19] Fleig O,Arakawa C.Large-eddy simulation of tip vortex flow at high Reynolds number.42nd AIAA Aerospace Science Meeting and Exhibit,2004.
[20] Roger M,Moreau S.Back-scattering correction and further extension of Amiet's trailing-edge noise model.Part I: theory.Journal of Sound and Vibration,2005,286(3): 477-506.
/
| 〈 |
|
〉 |
CJA