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超音喷流啸音的大涡模拟研究

发表时间:2010-03-31  浏览量:2033  下载量:1036
全部作者: 高军辉,李晓东
作者单位: 北京航空航天大学能源与动力工程学院
摘 要: 采用计算气动声学方法和大涡模拟(large eddy simulation, LES)策略数值模拟了马赫数为1�190和1�372的全三维圆管喷流啸音现象。主控方程采用Navier�Stokes方程,大涡模拟模型采用标准Smagorinsky亚格子模型。空间离散采用频散相关保持(dispersion�relation�preserving, DRP)格式,并采用10阶空间滤波方法滤掉格点伪波以保持计算的稳定,时间离散采用两层存储形式的低频散低耗散五六步Runge�Kutta法。在不同边界处采用适合其流动特点的无反射边界条件。数值模拟预测的啸音频率和幅值与PONTON等人的实验结果以及作者之前的非定常雷诺平均(unsteady Reynolds averaged Navier�Stokes, URANS)数值模拟结果进行了对比。
关 键 词: 航空宇航推进理论与工程;超音喷流啸音;计算气动声学;大涡模拟
Title: Large eddy simulation of the supersonic circular jet screech tones
Author: GAO Junhui, LI Xiaodong
Organization: School of Jet Propulsion, Beihang University
Abstract: In this paper, the full 3D supersonic circular jet screech tones at Mach number 1.190 and 1.372 are studied using large eddy simulation (LES) method. The Favre filterd Navier�Stokes equations are utilized as the governing equations, which are closed with the standard Smagorinsky subgrid model. The 7 points dispersion�relation�preserving (DRP) scheme is applied for spatial discretization, and a 10th order spatial filter is utilized every step to filter out the spurious waves in the computation. The low dissipation and low dispersion Runge�Kutta method in 2N storage form is used for time integration. Proper non�reflective boundary conditions are used at different boundary regions. The program simulates the screech phenomenon correctly. The simulated screech frequency and amplitude are compared with the experimental data of PONTON et al and the unsteady Reynolds averaged navier�Stokes (URANS) results of the present authors.
Key words: aerospace propulsion theory and engineering; supersonic jet screech tones; computational aeroacoustics; large eddy simulation
发表期数: 2010年3月第6期
引用格式: 高军辉,李晓东. 超音喷流啸音的大涡模拟研究[J]. 中国科技论文在线精品论文,2010,3(6):536-540.
 
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