## 3 Results and Discussion  
The Computational Fluid Dynamics analyses of four unmanned aerial vehicles with a swarm configuration were performed in this research, and the resulting data were evaluated. The processing of CFD results is referred to as post-processing, and this procedure was carried out using CFD-Post (v19) software. Due to factors such as mesh characteristics and solution methods, numerical discrepancies may occur in CFD results. Additionally, in the CFD-Post software, data regions were defined using Pearl, CCL, and CEL programming languages to facilitate visualization and graphing. First, all data lines were generated to create the plots of CFD results. Figure 4 displays these data lines, which were obtained from both horizontal and vertical lines drawn over the front and rear propeller axes. Plots obtained over the front propeller's axes are labeled with the \"F\" identifier, while those obtained over the rear propeller's axes are labeled with the \"B\" identifier. Additionally, the same colors which are used in the data lines are used in the plots as well. There may be differences in the data taken over the front and rear propeller's axes. Therefore, the data obtained over the front propeller's axes were chosen to align with the overall structure. In Figure 4, horizontal lines and planes representing the Y general coordinate values are displayed on the left side. In these horizontal data lines, the range of X values was taken from 100 cm to 465 cm, and the Z value was taken as 245 cm (F) or 220 cm (B). Additionally, on the upper side of the figure, vertically created data lines are shown together with X values. In the vertical lines, the Y variables were taken within the range of 0 cm to 1000 cm, and the Z variables were taken as either 245 or 220; the X variables were taken same values in the figure. The propeller axes X220, X245, X320, and X345 shown in the top-left and top-right of Figure 4 correspond to UAV-1 and UAV-2. All plots and contours were generated using these definitions. Figure 5 depicts the contours of velocity distributions in planes defined by the front and rear propeller axes as well as the midpoint of the UAVs. Figure 5a represents the contours from the rear propeller plane, Figure 5b from the midplane of the UAVs, and Figure 5c from the front propeller plane. In the velocity distribution, UAVs positioned below were affected by the airflow generated by the UAVs positioned above. When examining the velocity contours, it has been determined that velocity distributions approximately 2.5-3 m below the UAVs exhibited homogeneity along the propeller axes and vertical axes taken between the UAVs. Velocity distributions are shown by taken over the horizontal lines in Figure 8 and taken over the vertical lines in Figure 9. It has been observed that a phenomenon similar to the \"Near-field mixing phenomenon\", which occurs in near-jet \begin{table}
\begin{tabular}{l c c c c} \hline \hline
**Variables** & **X** & **Y** & **Z** & **Rev** \\ \hline
**Unit** & **m** & **m** & **m** & **RPM** \\ \hline UAV-1 Propeller Rear-Left & 2.2 & 6.2 & 2.2 & \(-\)10,000 \\ UAV-1 Propeller Rear-Right & 2.45 & 6.2 & 2.2 & 10,000 \\ UAV-1 Propeller Front-Left & 2.2 & 6.2 & 2.45 & 10,000 \\ UAV-1 Propeller Front-Right & 2.45 & 6.2 & 2.45 & \(-\)10,000 \\ UAV-2 Propeller Rear-Left & 3.2 & 6.2 & 2.2 & \(-\)10,000 \\ UAV-2 Propeller Rear-Right & 3.45 & 6.2 & 2.2 & 10,000 \\ UAV-2 Propeller Front-Left & 3.2 & 6.2 & 2.45 & 10,000 \\ UAV-2 Propeller Front-Right & 3.45 & 6.2 & 2.45 & \(-\)10,000 \\ UAV-3 Propeller Rear-Left & 2.2 & 5.45 & 2.2 & \(-\)10,000 \\ UAV-3 Propeller Rear-Right & 2.45 & 5.45 & 2.2 & 10,000 \\ UAV-3 Propeller Front-Left & 2.2 & 5.45 & 2.2 & 10,000 \\ UAV-3 Propeller Front-Left & 2.2 & 5.45 & 2.2 & 10,000 \\ UAV-4 Propeller Rear-Right & 3.45 & 5.45 & 2.45 & \(-\)10,000 \\ UAV-4 Propeller Front-Left & 3.2 & 5.45 & 2.2 & 10,000 \\ UAV-4 Propeller Front-Left & 3.45 & 5.45 & 2.45 & 10,000 \\ \hline \hline \end{tabular}
\end{table}