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论文:2012,Vol:30,Issue(5):779-783 |
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引用本文: |
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彭小波, 李林, 李佳明, 胡春波. 高温超音速喷流噪声场分布特性研究[J]. 西北工业大学 |
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Peng Xiaobo, Li Lin, Li Jiaming, Hu Chunbo. Effectively Determining Some Characteristics of Hot Supersonic Jet Noise Field Distribution[J]. Northwestern polytechnical university |
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高温超音速喷流噪声场分布特性研究 |
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彭小波, 李林, 李佳明, 胡春波 |
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西北工业大学 航天学院, 陕西 西安 710072 |
摘要: |
为了研究高温超音速喷流噪声特性,针对高温超音速喷流流场进行三维非稳态数值模拟,根据其湍流结构确定声源面并通过FW-H方程求解远场某点的声压级分布,分析高温超音速喷流噪声场分布规律以及喷管出口马赫数对喷流噪声场的影响。研究表明,该方法得到的计算结果与试验结果基本吻合,高温超音速喷流噪声具有很强的指向性;在特定工况下声压级峰值高达150 dB以上,喷管出口马赫数从2.5增加到3.0,相同观测点的声压级峰值增高10 dB左右。 |
关键词:
气动噪声
计算
可压缩流动
计算流体动力学
数值模拟
数值方法
火箭发动机
超音速空气动力学
三维
非稳态流动
出口马赫数
超音速喷流
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Effectively Determining Some Characteristics of Hot Supersonic Jet Noise Field Distribution |
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Peng Xiaobo, Li Lin, Li Jiaming, Hu Chunbo |
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College of Astronautics,Northwestern Polytechnical University,Xi'an 710072,China |
Abstract: |
We study noise characteristics of hot supersonic jet and simulate the 3-D unsteady supersonic hot jetflows.Sections 1 and 2 of the full paper explain our determination of some characteristics as mentioned in the title, which we believe is effective.Section 1 is entitled"Numerical Simulation of Plume Flow Field" ; its 3 subsectionsare respectively entitled "Physical Model"(1.1), "Grid Division and Boundary Conditions"(1.2), and"AcousticMethods"(1.3).Section 2 is entitled"Analysis of calculated results".Subsection 2.1 is entitled"Verification ofCalculation methods"(see Fig.4).The remaining 3 subsections are respectively entitled"Calculated Results ofFlow Field"(2.2)."Distribution of Acoustic Field"(2.3), and"Effects of Different Exit Mach Numbers on A-coustic Field"(2.4).The numerical simulation results, presented in Fig.5 through 9 and Tables 1 and 2, andtheir analysis show that: (1) the results got by the method fit test data and the high temperature supersonic jetnoise has very strong directionality; (2) under certain conditions, the peak sound pressure level is as high as 150dB; (3)when nozzle exit Mach number increased from 2.5 to 3.0, the peak sound pressure level increased by a-bout 10 dB at the same observation point. |
Key words:
acoustic noise
calculations
compressible flow
computational fluid dynamics
computer simulation
numerical methods
rocket engines
supersonic aerodynamics
three dimensional
unsteady flow;exitMach number
supersonic jet
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收稿日期: 2011-11-01
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DOI: |
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作者简介: 彭小波(1972-),西北工业大学博士研究生,主要从事航空宇航科学与技术研究。
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参考文献: |
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[1] Seiner J M,Ponton M K.The Effects of Temperature on Supersonic Jet Noise Emission.AIAA-1992-2046 [2] Gilles Rahier,Jean Prieur.Investigation of Integral Surface Formulations for Acoustic Post-Processing of Unsteady AerodynamicJet Simulations.Aerospace Science and Technology,2004,8: 453-467 [3] Lupoglazoff N,Biancherin A.Comprehensive 3D Unsteady Simulations of Subsonic and Supersonic Hot Jet Flow Field,PartI:Aerodynamic Analysis.AIAA-2002-2599 [4] Lupoglazoff N,Biancherin A.Comprehensive 3D Unsteady Simulations of Subsonic and Supersonic Hot Jet Flow Field,PartII:Aerodynamic Analysis.AIAA-2002-2600 [5] Brenton J Greska.Supersonic Jet Noise and Its Reduction Using Microjet Injunction.The Florida State University Famu-FsuCollege of Engineering,2005 [6] 庄家煜,李晓东.喷流噪声控制方法实验研究.工程热物理学报,2008,29(4): 587-590Zhuang Jiayu,Li Xiaodong.An Experimental Study of Jet Noise Suppression Methods.Journal of Engineering Thermophysics,2008,29(4): 587-590 (in Chinese) [7] Ffowcs Williams J E,Hawkings D L.Sound Generated by Turbulence and Surfaces in Arbitrary Motion.Philosophical Transac-tions of the Royal Society,1969,A264(1151): 321-342 |
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