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헥사콥터의 제자리 비행 시 후류 특성에 관한 수치해석

원문정보

A Numerical Analysis of Wake Characteristics in Hovering Flight of Hexa-copter

정원훈, 김나용, 김동건, 김봉환

피인용수 : 0(자료제공 : 네이버학술정보)

초록

영어

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.

목차

ABSTRACT
1. 서론
2. 헥사콥터 및 프로펠러 특성
3. 프로펠러 간 상호간섭 공력해석
3.1 유동 지배방정식과 유동해석 모델
3.2 경계조건 및 해석변수
3.3 해석 결과
4. 동체 영향에 대한 공력해석
4.1 해석 모델 및 격자 생성
4.2 경계조건 및 해석 결과
4.3 헥사콥터의 추력 주기 및 와류구조
5. 결론
References

저자정보

  • 정원훈 Won-Hoon Jeong. Automotive Engineering Department, Graduate School, Gyeongsang National University
  • 김나용 Na-Young Kim. Automotive Engineering Department, Graduate School, Gyeongsang National University
  • 김동건 Dong-Keon Kim. Automotive Engineering Department, Gyeongsang National University
  • 김봉환 Bong-Hwan Kim. Automotive Engineering Department, Gyeongsang National University

참고문헌

자료제공 : 네이버학술정보

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