双喉道喷管与飞翼布局无人机气动数值研究  

Research on Dual Throat Fluidic Thrust Vectoring Nozzle and Flying Wing Layou UAV

作　　者：母鸿瑞 杨青真[1] 邓雪姣[1] 金大鑫[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《航空计算技术》2014年第1期90-93,共4页Aeronautical Computing Technique

基　　金：航空科学基金项目资助(2011ZA06001)

摘　　要：利用超椭圆方法,设计了双喉道射流矢量喷管的气动外形,并采用S-A湍流模型数值研究了次主流压比、次流方向及喷管外形参数对其气动特性的影响。研究表明,当确定次主流压比SPR=3时,可依次确定该型喷管外形参数分别为空腔长度l=3h,空腔扩张角θ1=10°,空腔收敛角θ2=30°,二次流注入角α=120°时,矢量喷管的气动特性最优。将设计的气动最优喷管与飞翼布局无人机后体进行一体化设计,数值模拟了喷管对飞翼布局无人机升阻特性的影响,结果表明,双喉道射流矢量喷管能够很好地运用于飞翼布局无人机。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 a- dopting 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 ba- sis, 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.

关 键 词：双喉道 矢量喷管 外形参数 气动特性 数值模拟 升阻特性 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]