论文:2012,Vol:30,Issue(5):779-783
引用本文:
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
Peng Xiaobo, Li Lin, Li Jiaming, Hu Chunbo. Effectively Determining Some Characteristics of Hot Supersonic Jet Noise Field Distribution[J]. Northwestern polytechnical university

高温超音速喷流噪声场分布特性研究
彭小波, 李林, 李佳明, 胡春波
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   
Effectively Determining Some Characteristics of Hot Supersonic Jet Noise Field Distribution
Peng Xiaobo, Li Lin, Li Jiaming, Hu Chunbo
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   
收稿日期: 2011-11-01     修回日期:
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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