Direct Numerical Simulation of Acoustic Noise Generation from the Nozzle Wall of a Hypersonic Wind Tunnel
Direct Numerical Simulation of Acoustic Noise Generation from the Nozzle Wall of a Hypersonic Wind Tunnel
复制标题
高超声速风洞喷嘴壁产生声学噪声的直接数值模拟
DOI：
10.2514/6.2017-3631
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发表时间：
2017
期刊：
影响因子：
--
通讯作者：
L. Duan
中科院分区：
文献类型：
--
作者：
Junji Huang;L. Duan
采用直接数值模拟（DNS）方法，在布伦瑞克（HLB）马赫数6高超声速路德维希管工作范围内，对马赫数6路德维希管喷管壁面湍流边界层声辐射进行了数值模拟。壁面边界层的平均和湍流统计数据与Pate关联式和雷诺平均Navier-Stokes（RANS）计算的结果吻合良好。均方根压力脉动p（cid：48）rms /τ w在喷管的自由涡核处趋于平稳。喷管内的自激噪声强度比具有相同自激马赫数的单个喷管辐射的噪声强度高约20%，这可能是由于喷管壁的多个方位角段对声辐射的贡献
The acoustic radiation from the turbulent boundary layer on the nozzle wall of a Mach 6 Ludwieg Tube is simulated using Direct Numerical Simulations (DNS), with the flow conditions falling within the operational range of the Mach 6 Hypersonic Ludwieg Tube, Braunschweig (HLB). The mean and turbulence statistics of the nozzle-wall boundary layer show good agreement with those predicted by Pate’s correlation and Reynolds Averaged Navier-Stokes (RANS) computations. The rms pressure fluctuation p (cid:48) rms /τ w plateaus in the freestream core of the nozzle. The intensity of the freestream noise within the nozzle is approximately 20% higher than that radiated from a single flat pate with a similar freestream Mach number, potentially because of the contributions to the acoustic radiation from multiple azimuthal segments of the nozzle wall