摘要
根据短喷管设计理论,获得了可以考虑进口气流带攻角、并直接针对非对称喷管构型的设计程序。通过改变喷管上下壁面进口处的气流初始膨胀角之比F和喷管进口气流方向角α,可以得到一系列不同的非对称喷管外型。文章用FLUENT软件对设计得到的喷管进行了无粘流场验证,证明了设计的合理性。又根据实际飞行马赫数为6的设计条件,设计了一系列对应的喷管,用CFD方法对不同的喷管进行了流场数值模拟,并进行了截短后流场计算。计算结果表明:参数F和截短对喷管性能影响显著。
The designing method of SERN is provided,which is based on the theory of characteristics,to obtain the optimum length nozzle.By changing the ratio of initial expansion angle F and flow direction angle α,a series of two-dimensional,length-optimized configurations are obtained.In order to verify the design method,2-D inviscid nozzle flow field is numerically simulated by means of FLUENT software.Under the condition of Mach number 6 free stream,different nozzle configurations with different geometric parameters（F） are obtained.The flow fields of these different nozzle configurations are numerically studied.Furthermore,the ＂cutting down＂ effect on the SERN performance is numerically simulated.The numerical results reveal that both parameter F and ＂cutting down＂ evidently affects the nozzle performance.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2007年第3期282-286,共5页
Journal of Propulsion Technology
基金
国家"八六三"计划资助(2002AA723011)
关键词
喷管
数值仿真
高超声速
设计
Nozzle
Numerical simulation
Hypersonic
Design
