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.%We study noise characteristics of hot supersonic jet and simulate the 3-D unsteady supersonic hot jet flows. 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 subsections are respectively entitled" Physical Model" (1.1), " Grid Division and Boundary Conditions" (1.2), and " Acoustic Methods" (1.3). Section 2 is entitled "Analysis of calculated results". Subsection 2. 1 is entitled "Verification of Calculation methods" (see Fig. 4). The remaining 3 subsections are respectively entitled "Calculated Results of Flow 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, and their analysis show that: (1) the results got by the method fit test data and the high temperature supersonic jet noise has very strong directionality; (2) under certain conditions, the peak sound pressure level is as high as 150 dB; (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.
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