摘要
We utilize the nonlinear acoustic solver(NLAS)and Ffowcs-Williams/Hawkings(FW-H)equation to investigate the noise generation and radiation due to shock(wave)and boundary layer interaction(SBLI)in the inlet duct.A classical benchmark for SBLI is chosen to validate the flow features and numerical results show good agreement with experimental results.In the simulation of the noise generated by SBLI,the inlet buzz phenomenon is successfully observed.The oscillation of the normal shock is a kind of little buzz and the oscillation of inner shocks is a kind of big buzz with a frequency around 100 Hz.In the far-field,frequency spectrums show a dominant frequency close to the frequency of inner shocks oscillation.This indicates that the oscillation of inner shocks determines the magnitude of the overall sound pressure level(OASPL)of the far-field noise.
我们采用非线性声学求解器(NLAS)和Ffowcs-Williams/Hawkings(FW-H)方程对飞机进气道中由激波边界层干扰产生的噪音进行了数值研究.一个关于激波边界层干扰的标模问题用于验证流场特征,数值结果与实验结果有很好的一致性.在模拟激波边界层干扰产生噪音的过程中,我们成功的观察到了喘振现象.正激波的震荡是一种小喘振,而内激波的震荡是一种大喘振,频率大约为100 Hz.远场噪音频谱表明远场噪音的主导频率与内激波震荡的频率很接近,这说明,内激波震荡决定了远场噪音的总声压级的量级.
作者
Yuanjun Dai
Yiran An
Zhi Li
Qunfeng Zhang
戴袁鋆;安亦然;李植;张群峰(Department of Mechanics and Engineering Science,College of Engineering,Peking University,Beijing 100871,China;School of Civil Engineering,Beijing Jiaotong University,Beijing 100044,China)
基金
This work was supported by the National Natural Science Foundation of China(Grant No.11772314)
the Basic Research Program(Grant No.JCKY2018204b054).
