超音喷流啸音的大涡模拟研究
首发时间:2009-01-21
摘要:本文采用计算气动声学方法和大涡模拟策略数值模拟了马赫数为1.19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等人的实验结果对比符合得很好。与作者之前的非定常雷诺平均数值模拟结果相比,大涡模拟结果无论在啸音波长还是幅值上都更接近实验结果。
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Large Eddy Simulation of the Supersonic Circular Jet Screech Tones
Abstract:In this paper, the full 3D supersonic circular jet screech tones at Mach number 1.19 and 1.372 are studied using Large eddy simulation 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 time 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 simulated the screech phenomenon correctly. The simulated screech frequency and amplitude agree well with the experimental data of Ponton et al. Comparing with the URANS results of the present authors, it is shown that the LES simulated screech wavelength and amplitude agree better with the experimental data than the URANS results.
Keywords: Supersonic Jet Screech Tones Computational Aeroacoustics Large Eddy Simulation
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