한국전산유체공학회지 (Journal of computational fluids engineering)

한국전산유체공학회 (Korean Society of Computational Fluids Engineering)
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정지비행 로터 블레이드에 부착된 탭의 공기역학적 효과

AERODYNAMIC EFFECTS OF THE TAB ON A HOVERING ROTOR BLADE

  • 강희정 (한국항공우주연구원 회전익기술팀) ;
  • 김도형 (한국항공우주연구원 회전익기술팀) ;
  • 김승호 (한국항공우주연구원 회전익기술팀)
  • Kang, H.J. (Korea Aerospace Research Institute, Rotor Team) ;
  • Kim, D.H. (Korea Aerospace Research Institute, Rotor Team) ;
  • Kim, S.H. (Korea Aerospace Research Institute, Rotor Team)
  • 투고 : 2013.07.15
  • 심사 : 2013.08.26
  • 발행 : 2013.09.30
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초록

Numerical simulation was performed for the rotor blade with fixed tab in hover using an unstructured mesh Navier-Stokes flow solver. The inflow and outflow boundary conditions using 1D momentum and 3D sink theory were applied to reduce computational time. Calculations were performed at several operating conditions of varying collective pitch angle and fixed tab length. The aerodynamic effect of fixed tab length was investigated for hovering efficiency, pitching moment and flapping moment of the rotor blade. The results show that it affects linearly increasing on the pitching moment of the rotor blade but does not affect on the flapping moment. The required power is less than 45kw for ground rotating test in hover. Numerical simulations also show that the vortex generate not only from the tip of the rotor blade but also from the fixed tab on the rotor blade.

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참고문헌

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피인용 문헌

  1. 회전 효과를 고려한 Active Gurney Flap 의 동특성 해석 vol.3, pp.3, 2013, https://doi.org/10.3795/ksme-c.2015.3.3.183