Abstract
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. The freestream is 50m/s over –4 to 26 degree A.o.A.s. Reynolds number based on the mean chord length is × . 3D multi block hexahedral grids are used which allow good grid quality and ease to capture boundary layer. model as well as SST model is employed to assess the effect of transition for flow behavior. Drag and lift of the UCAV were well predicted while is under predicted at high angle of attacks and influenced by the turbulence models strongly. After assessing pressure distribution, skin friction lines and velocity field around the UCAV configuration, it was found that transition effect should be considered to enhance the prediction of aerodynamic behavior by a vortical flowfield.
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