摘要
在S弯进气道设计点,针对前机身/进气道一体化模型,采用CFD数值模拟技术开展内外流计算,分析管道内流场特性从而为流动控制装置设计提供参考依据。采用微质量射流流动控制装置对进气道内流进行流动控制,射流装置可变参数包括射流装置安装站位、入射流向角度、侧向角度及射流孔间距。基于DOE方法设计控制效能计算样本,开展流动控制效能计算分析,得到总压恢复系数σ及流场畸变指标DC60的响应面函数,采用多目标优化技术,得到使得总压恢复比较高、流场畸变比较小的控制装置参数Pareto最优解。
CFD simulation was conducted to simulate inner and outer lfow ifelds of S-shape inlet on design points for fore-fuselage and inlet integration model, and inner flow field performance was analyzed to provide referent basis to lfow control device design. Micro-mass jet control device was adopted to control inlet inner lfow ifeld, with changeable parameters： device installation location, inlfow stream-wise angles, lateral angles and the spaces between jet oriifces. Flow control efifciency computation samples were designed based on DOE method, and control efifciency computation analysis was conducted to get the response surface function of total pressure recovery coefficientσ and flow field distortion index DC60. Multi-objectives technology is used to obtain the Pateto optimum solution of control device parameter with higherσand DC60 lower .
出处
《航空科学技术》
2015年第8期67-72,共6页
Aeronautical Science & Technology
基金
航空科学基金(20111226006)~~
关键词
S弯进气道
微质量射流
总压恢复
畸变
隐身无人机
飞翼
多目标优化
S-shape inlet
micro-mass jets
total pressure recovery
distortion
stealth UAV
all-wing aircraft
multiobjectives
optimization
