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BWB UCAV 형상 주변의 유동해석에 대한 천이모델의 예측능력 연구
조영희(Y.H. Jo),장경식(K.S. Chang),신동진(D.J. Sheen) 한국전산유체공학회 2014 한국전산유체공학회 학술대회논문집 Vol.2014 No.11
A computational simulation for a nonslender BWB UCAV configuration with rounded leading edge and span of 1.0m was performed to analyze its aerodynamic characteristics at low A.o.A.s. Reynolds number based on the mean chord length is 1.25 million. γ-Re<SUB>θ</SUB> transition model and k-ω SST model was used to assess effect of transition for flow behavior. Also γ transition model that accounts for crossflow instability effects was employed to investigate crossflow instability effects in three-dimensional boundary layer on the UCAV aerodynamic surfaces. After assessing aerodynamic coefficients and lift to drag, it was found that crossflow effects plays an important roles at given flow condition.
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연속일체형 날개-동체 타입 UCAV 형상의 저속 종방향 공력특성에 대한 전산유동해석
박상현(S.H. Park),장경식(K. Chang),심호준(H.J. Shim),신동진(D.J. Sheen),박수형(S.H. Park) 한국전산유체공학회 2016 한국전산유체공학회지 Vol.21 No.3
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, γ 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.
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