摘要
为研究高超声速飞行器后体喷管三维构型的设计,以NASA半壁喷管试验为参考,进行了二维及三维内外流相互作用的数值模拟计算,分析了后体喷管三维流场的特点.从高超声速飞行器机身推进一体化的角度,构建了后体喷管三维构型,进行了不同构型设计对后体喷管性能影响的参数研究.结果表明:后体喷管的三维效应不可忽视,后体喷管侧壁的存在及下壁面长度对性能影响较大.
Three dimensional configuration design of afterbody/nozzle was studied in this paper. Flow filed numerical simulations were conducted on NASA single expansion ramp nozzle experiment model. Numerical simulation results of two-dimensional and three-dimen- sional flow field without/with side fence were compared with experiment data and structure of three-dimensional flow filed. From the viewpoint of hypersonic vehicle airframe/propulsion integrated design, three-dimensional configuration of afterbody/nozzle was constructed with side fences. Parameters of cowl length and side fence inclination angle were investigated to analyze their effects on thrust, lift and pitch moment acted on overall vehicle. The results show three dimensional effect of afterbody/nozzle flow field could not be neglected.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第2期247-254,共8页
Journal of Aerospace Power
基金
中国博士后科学基金(20070420285)
关键词
高超声速飞行器
一体化设计
后体喷管
三维构型
数值模拟
hypersonic vehicle
integrated design
afterbody/nozzlethree-dimensional configuration
numerical simulation
