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.

Abstract
1. 서 론
2. 헥사콥터에 대한 유동해석
    2.1 유동 지배방정식
    2.2 유동해석 모 델
    2.3 격자 생성 및 경계조건
3. 해석결과 및 고찰
5. 결 론
References

• 김나용(Graduate School, Gyeongsang National University) | Na-Yong Kim
• 이치우(Department of Future Automotive Engineering, Gyeongsang National University) | Chi-Woo Lee Corresponding author