한국전산유체공학회지 (Journal of computational fluids engineering)

한국전산유체공학회 (Korean Society of Computational Fluids Engineering)
권호 표지
DOI QR코드

DOI QR Code

연속일체형 날개-동체 타입 UCAV 형상의 저속 종방향 공력특성에 대한 전산유동해석

COMPUTATIONAL FLUID DYNAMICS OF THE LOW-SPEED LONGITUDINAL AERODYNAMIC CHARACTERISTICS FOR BWB TYPE UCAV CONFIGURATION

  • 박상현 (한서대학교 항공시스템공학과) ;
  • 장경식 (한서대학교 항공기계학과) ;
  • 심호준 ((주)한화 종합연구소 대공체계팀) ;
  • 신동진 (한서대학교 항공기계학과) ;
  • 박수형 (건국대학교 항공우주정보시스템학과)
  • Park, S.H. (Dept. of Aerosystem Engineering, Hanseo Univ.) ;
  • Chang, K. (Dept. of Aeromechanical Engineering, Hanseo Univ.) ;
  • Shim, H.J. (Hanhwa Corporation R&D Center, Surface-to-Air System) ;
  • Sheen, D.J. (Dept. of Aeromechanical Engineering, Hanseo Univ.) ;
  • Park, S.H. (Dept. of Aerospace Information Engineering, Konkuk Univ.)
  • 투고 : 2016.06.08
  • 심사 : 2016.09.13
  • 발행 : 2016.09.30
PDF 다운로드
⟨ 이전 논문 다음 논문 ⟩

초록

In the present work, numerical simulations were conducted on the scaled model of the BWB type UCAV in the subsonic region using ANSYS FLUENT V15. The prediction method was validated through comparison with experimental results and the effect of the twisted wing was investigated. To consider the transitional flow phenomenon, ${\gamma}$ transition model based on SST model was adopted. The coefficients of lift, drag and pitching moment were compared with experimental results and the pressure distribution and streamlines were investigated. The twisted wing decreases the lift force but increases lift-to-drag ratio through delay of stall and leading edge vortex's movement to the front, also the non-linearity of the pitching moment is decreased.

키워드

참고문헌

  1. 2008, Khalid, M., Yuan, W. and Zhang, F., "A CFD study of UCAV 1303 baseline model at cruise mach numbers," 26th International congress of the aeronautical science.
  2. 2011, Anderson, J.D.JR., "Fundamental of aerodynamics," Fifth edition, Ch.5 pp.461-475.
  3. 2001, ESDU, "Effect of planform geometry on low speed pitch-break characteristics of swept wings," ESDU international, Item No.01005.
  4. 2006, Crippa, S. and Rizzi, A., "Numerical Investigation of Reynolds Number Effects on a Blunt Leading-Edge Delta Wing," AIAA-2006-3001.
  5. 1996, Chu. J. and Luckring, J.M., "Experimental surface pressure data obtained on $65^{\circ}$ delta wing across Reynolds number and Mach number ranges," NASA TM 4545.0.
  6. 1993, Mondoloni, S.L., "A numerical method for modelling unsteady wings with sharp edges maneuvering at high angles of attack," Doctor of Philosophy, MASSACHUSETTS INSTITUTE OF TECHNOLOGY.
  7. 2015, Shim, H.J., "An experimental study on wake characteristics of vane-type vortex generator and its application," Ph. D. Thesis, KAIST.
  8. ANSYS FLUENT USER's Guide.
  9. 2014, Menter F.R. and Smirnov, P., "Laminar-turbulent transition modeling based on a new intermittency model formulation," 11th World Congress on Computational Mechanics.

피인용 문헌

  1. 날개의 비틀림이 동체-날개 융합익형 무인전투기의 종안정성에 미치는 영향에 대한 연구 vol.46, pp.1, 2018, https://doi.org/10.5139/jksas.2018.46.1.1
  2. CFD Analysis of the Sideslip Angle Effect around a BWB Type Configuration vol.2019, pp.None, 2019, https://doi.org/10.1155/2019/4959265