CFD OF BLENDED WING BODY UCAV WITH VORTEX GENERATOR

摘要

The present work performed the numerical simulation for the BWB type UCAV configuration using CFD. In BWB configuration, the stability problem due to the pitch –break or the pitch-up occurs in a region of high angle of attack during take-off or landing. To overcome this instability, the vortex generator was considered and the effect of this stabilizer on the aerodynamic force and moment coefficients was validated using CFD based on the experimental results. Also the delay of the pitch-break was confirmed by the vortex generator through the simulation.