有无涵道动力下的类BWB低速布局气动特性研究

随着航空飞行器的不断发展,新型非常规气动布局研究早已成为世界航空大国的关注焦点。基于TRIP 3.0软件平台通过等效盘模型应用到涵道风扇内外流一体化模拟中,完成对类BWB低速布局有无涵道风扇动力下的气动特性和流场影响分析。首先,对某单独螺旋桨验证算例进行分析;然后,对单独涵道风扇进行计算,得到设计推力下的涵道动力叶片数、安装角及转速等参数;最后,将设计推力下涵道动力参数应用到类BWB低速布局全机有无动力模拟中。结果表明:计算拉力和扭矩值与试验值吻合较好;尾部布置的涵道动力对机身后段及尾翼压力分布影响显著;涵道对前方气流抽吸作用,加速机身后段上表面气流流速,减小内侧平尾有效迎角,对机身和平尾升力以及俯仰力矩系数影响较大;在小迎角状态下,涵道动力对机身增升作用明显,会产生明显低头力矩,但对平尾作用正好相反,且两者增量大小相当,使得全机增升效果不显著,且俯仰力矩变化较小。

Aerodynamic Characteristics of BWB Analog Low-Speed Aerodynamics Configuration with and without Ducted Fan

The actuator disk model applied in ducted fan based on self-developed "TRI sonic Platform"(TRIP 3.0) is developed, and the aerodynamic characteristics of BWB analog low-speed aerodynamics configuration with and without ducted fan are analyzed. Firstly, the computational results of thrust and torque of a single propeller are in good agreement with the testing data. Secondly, in order to achieve the designed fan thrust, the key parameters of blade number, mounting angle and rotational speed of a isolated ducted fan are calculated. Finally, applied the key parameters in ducted fan of aircraft, a BWB analog low-speed aerodynamics configuration with and without ducted fan are presented. The results show that pressure coefficients distribution at fuselage and tail had obvious effect with ducted fan compared to without fan. By sucking the forward flow with ducted fan, the flow speed above the fuselage was increased and the angle of attack of horizontal tail was decreased. Therefore, the lift and pitching moment coefficients of fuselage and horizontal tail influenced by with and wihout fan were obvious. Otherwise, in the range of little angle of attack, with the effect of ducted fan, the lift and pitching moment of fuselage is increased and horizontal tail is decreased, but for the entire aircraft, the different of lift and pitching moment coefficients with and without ducted fan is comparatively small.