In this study, flow analysis was performed using ANSYS CFX to evaluate the performance of the 30kg hydrogen fuel cell hexa-copter drone in hovering flight. In the case of a hydrogen fuel cell hexa-copter drone, a total of four cooling fans are mounted on the drone's body in two pairs on the left and right to cool the fuel cell module. In order to evaluate the effect of the air flow from the cooling fan on the aerodynamic properties of the hydrogen fuel cell drone as the mounted cooling fan operates, the change in thrust for the case where the cooling fan operates and does not operate was compared and analyzed. Looking at the analysis results, it was found that the presence or absence of the drone's cooling fan had little effect on the drone's thrust through the thrust results for the six wings.

In this study, a numerical analysis was performed as steady-state analysis to investigate the effect of interference between the propellers of the hexa-copter. As the distance increases, there is little change in thrust, but when a propeller close to the reference propeller rotates, it was confirmed that the thrust decreased due to the interference effect. Unsteady state analysis was performed to confirm the influence of the hexa-copter fuselage. If there is a fuselage, the thrust was predicted to increase by about 4.97% due to the ground effect. If the design parameters are established considering the effect of the fuselage of the hexa-copter, it is expected to be used for basic design and application design in the future.