Research on Dual Throat Fluidic Thrust Vectoring Nozzle and Flying Wing Layou UAV
MU Hong-rui;YANG Qing-zhen;DENG Xue-jiao;JIN Da-xin;School of Power and Energy,Northwestern Polytechnical University;
Base on the hyper elliptic method,the dynamic contour of a dual throat fluidic thrust vectoring nozzle was designed,and the numerical research on the effect second fluid pressure ratio,the secondary fluid inject direction and the geometric parameters to the aerodynamic characteristics was carried out adopting the S-A turbulence model. The results show that the optimal aerodynamic performance is obtained at the condition where second fluid pressure ratio SPR = 3,the cavity length l = 3h,cavity expansion angle θ1= 10°,cavity convergence angle θ2= 30°and the secondary flow injection angle α = 120°. On this basis,the aerodynamic optimum nozzle was selected for the integration design with the after body of all-wing aircraft layout UAV,and numerical simulation of the nozzle' s influence on the all- wing aircraft layout UAV lift-to-drag characteristics was carried out. The results show that the dual throat jet vectored nozzle can be well applied to the flying wing layout UAV.