## 5 Conclusions  
In this paper, based on the experimental data of Ref. [22], the effects of trailing edge shape and the corresponding modeling method, far-field distance, and turbulence model on the force coefficients under high Reynolds numbers are discussed. Section 2 introduces the applied modeling methods, grid divisions, turbulence models, and the numerical procedure. In Section 3, we confirm the appropriate grid strategy and the numerical \begin{table}
\begin{tabular}{c c c c c c c} \hline \hline \multirow{3}{*}{**Range of AOA(\({}^{\circ}\))**} & \multicolumn{6}{c}{**Type of NACA0012 Model**} \\ \cline{2-7}  & \multicolumn{6}{c}{**The Optimal Mean Error Ratios of (\(\mathbf{C_{d}}\))**} \\ \cline{2-7}  & \multicolumn{6}{c}{**Sharp Trailing Edge**} \\ \cline{2-7}  & \multicolumn{2}{c}{**Blunt Trailing Edge**} & \multicolumn{2}{c}{**NACA4**} & \multicolumn{2}{c}{**Formula (132 Points)**} & \multicolumn{2}{c}{**Formula (200 Points)**} & \multicolumn{2}{c}{**Formula (264 Points)**} & \multicolumn{2}{c}{**Formula (400 Points)**} \\ \hline (\(0^{\circ},0^{\circ}\)) & (0.21\%, 0.00\%) & (0.05\%, 0.00\%) & (0.02\%, 0.00\%) & (0.00\%, 0.00\%) & (0.01\%, 0.00\%) & (0.05\%, 0.00\%) \\ \cline{2-7}  & SST+16 m & SA+12 m & **SA+20 m** & SA+20 m & SA+20 m & SA+16 m \\ \hline (\(0^{\circ},2^{\circ}\)) & (1.02\%, 1.85\%) & (**0.78\%, 1.38\%**) & (1.03\%, 1.25\%) & (0.99\%, 1.25\%) & (1.03\%, 1.25\%) & (1.02\%, 1.25\%) \\ \cline{2-7}  & SST+12 m & **SST+20 m** & SST+12 m & SST+12 m & SST+12 m & SST+12 m \\ \hline (\(0^{\circ},4^{\circ}\)) & (3.43\%, 1.75\%) & (**2.80\%, 1.22\%**) & (2.81\%, 1.44\%) & (2.88\%, 1.43\%) & (2.82\%, 1.43\%) & (2.83\%, 1.42\%) \\ \cline{2-7}  & SST+20 m & **SST+20 m** & SST+20 m & SST+20 m & SST+20 m & SST+20 m \\ \hline (\(0^{\circ},6^{\circ}\)) & (5.63\%, 1.34\%) & (**4.98\%, 1.11\%**) & (4.93\%, 1.19\%) & (5.07\%, 1.20\%) & (4.94\%, 1.18\%) & (4.94\%, 1.18\%) \\ \cline{2-7}  & SST+20 m & **SST+20 m** & SST+20 m & SST+20 m & SST+20 m & SST+20 m \\ \hline (\(0^{\circ},8^{\circ}\)) & (6.52\%, 1.61\%) & (5.89\%, 1.55\%) & (5.75\%, 1.55\%) & (6.05\%, 1.58\%) & (5.78\%, 1.55\%) & (**5.75\%, 1.54\%**)** \\ \cline{2-7}  & SST+20 m & SST+20 m & SST+20 m & SST+20 m & SST+20 m & **SST+20 m** \\ \hline (\(0^{\circ},10^{\circ}\)) & (7.72\%, 1.65\%) & (7.50\%, 1.53\%) & (6.68\%, 1.56\%) & (7.16\%, 1.53\%) & (6.67\%, 1.55\%) & (**6.67\%, 1.55\%**)** \\ \cline{2-7}  & SA+20 m & SA+20 m & SA+20 m & SA+20 m & SA+20 m & **SA+20 m** \\ \hline \hline \end{tabular}
\end{table} 
Table 19: The optimal results and the corresponding simulation parameters. Figure 20: The optimal total error ratios of turbulence models and the corresponding calculation accuracy improvements. method. The shape of the trailing edge and related modeling method dependencies, the far-field distance dependencies, and the turbulence model dependencies under six AOA ranges are expressed in Section 4. In particular, the number of data points adopted into the definition formula dependencies is discussed. Through systematic analysis, several conclusions can be drawn, as follows:  
1. [label=0., ref=0]
2. nlike the choice of the trailing edge shape depending on the value of AOA under a lower Reynolds number, we should prioritize adopting the sharp trailing edge under a high Reynolds number. Therefore, the corresponding methods of NACA4 generator and the definition formula are suggested. The definition formula is preferred if the studied ranges are (0\({}^{\circ}\), 0\({}^{\circ}\)), (0\({}^{\circ}\), 8\({}^{\circ}\)), and (0\({}^{\circ}\), 10\({}^{\circ}\)). If this is not the case, the NACA4 generator is preferred. It should be noted that a greater number of data points adopted into the definition formula does not neccesarily imply better performance. On the one hand, this may reqiore more computing resources. On the other hand, as described in Section 4.7, the improvement in calculation accuracy is limited, and accuracy may even be reduced. 3.