摘要
为得到二维高超声速飞行器后体喷管优化型面,建立了基于N-S方程的二维后体喷管设计模型,分别对内部喷管长度和上壁型面进行设计,得到了后体喷管优化设计外形,并将结果与Edwards提供的基准进行比较,表明改进了后体喷管的推进性能.
A model based on numerical solution of Navier-Stokes equations was estab- lished for hypersonic flight vehicle nozzle afterbody optimization design. The internal portion and the upper wall of nozzle were designed, and the optimized configuration was obtained. The result was compared to the norm configuration that Edwards claimed. The results show that the performance of nozzle afterbody was improved.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第2期257-260,共4页
Journal of Aerospace Power
关键词
航空
航天推进系统
高超声速
后体喷管
数值模拟
膨胀波
aerospace propulsion system
hypersonic
nozzle afterbody
numericalsimulation
expansion wave
