Numerical simulation of the low speed aerodynamic characteristics for BWB type UCAV configuration with -5° twisted angle

摘要

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 washout wing was investigated. To consider the transitional flow phenomenon, γ transition model based on SST model was adopted. The coefficient of lift, drag and pitching moment were compared with experimental results and the pressure distribution and streamlines were investigated according to the angle of attack. The washout wing decreases the lift force but increase the 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.