## 3 Aerodynamic Noise Analysis of the Panel
### Incompressible Numerical Simulation
#### 3.1.3 Aerodynamic Noise Analysis
The vibro-acoustic model established by the method of random modal force and deterministic modal force is shown in \[J_{mn}^{2}(\omega)=\frac{\widetilde{\Phi}_{mn}(\omega)}{\Phi(\omega)S^{2}} \tag{10}\]4 The two FSPs represent the convective component and the acoustic component. SIF is used to capture the SPL at the receiving point. \[J_{mn}^{2}(\omega)=\frac{\widetilde{\Phi}_{mn}(\omega)}{\Phi(\omega)S^{2}} \tag{10}\]5 The model of Corcos model and DAF. \[J_{mn}^{2}(\omega)=\frac{\widetilde{\Phi}_{mn}(\omega)}{\Phi(\omega)S^{2}} \tag{10}\]6 Modes of the panel: (**a**) 153.2 Hz; (**b**) 398.49 Hz. \[J_{mn}^{2}(\omega)=\frac{\widetilde{\Phi}_{mn}(\omega)}{\Phi(\omega)S^{2}} \tag{10}\]7 Vibro-acoustic model of the random modal force and deterministic modal force. (c) Result Analysis  
The SPLs radiated from the position of 0.1 m away from the panel under the excitation of the Corcos model with and without the acoustic component are shown in \[J_{mn}^{2}(\omega)=\frac{\widetilde{\Phi}_{mn}(\omega)}{\Phi(\omega)S^{2}} \tag{10}\]8 In this figure, we can see that the radiated SPL of the panel with the excitation of the acoustic component is 2-5 dB higher than that of the panel without the excitation of the acoustic component at 2500 Hz. Thus, the excitation of the acoustic component has a great influence on the radiated SPL in high frequency band. In order to accurately predict the radiated noise of the panel under the FSP, the effect of the acoustic component cannot be neglected. Meanwhile, the radiated SPL has a peak at 3150 Hz, which shows the coincidence effect when the wavenumber of the panel is equal to the wavenumber of the acoustic component. The results of the radiated SPLs of the panel calculated by the random modal force coupling BEM and the deterministic modal force coupling BEM are shown in Figures 20 and 21. Likewise, we can see that the radiated SPL of the panel coupling the excitation of the acoustic component is higher than that of the panel without the excitation of the acoustic component. It is consistent with the calculation results of the Cocos Model coupling BEM model. In Figure 20, the peak value of the random modal force coupling the acoustic component occurs at 4000 Hz, and the radiated SPL is not only related to the magnitude of excitation, but also to the resonance of the panel. One of the resonance frequencies of the panel is 4006.7 Hz, so there is a large peak value of the radiated SPL by the panel at this frequency. Another peak at 400 Hz is due to the aerodynamic coincidence effect. \[J_{mn}^{2}(\omega)=\frac{\widetilde{\Phi}_{mn}(\omega)}{\Phi(\omega)S^{2}} \tag{10}\]9 Radiated SPLs of the panel under the Corcos model coupling DAF and only the Corcos model. \[S_{mn}\left(k_{x},k_{y}\right)=\frac{2}{\sqrt{ab}}\int_{0}^{a} \int_{0}^{b}sin(\frac{m\pi y}{a})sin(\frac{n\pi x}{b})e^{-ik_{x}x}e^{-ik_{y}y }dxdy \tag{11}\]0 Radiated SPLs of the panel under the random modal force with and without the acoustic component. In Figure 21, it is possible to appreciate that the difference between the results of the deterministic modal force with and without the excitation of the acoustic component is greater than that of the random modal force method. That is because the signal averaging and smoothing are performed by using the method of random modal force to make the signal more stable than the method of deterministic modal force.