摘要
采用实验设计(DOE)方法对影响超紧凑进气道流动控制效果的五个因素进行优化设计。采用数值源项模型代替真实物理叶片进行流场求解,分析了27组涡流发生器应用于进气道流动控制的效果,从中找出各影响因素变量对进气道总压恢复、流场畸变不同影响,应用响应曲面法给出最佳影响因素组合,为超紧凑进气道被动流动控制设计提供技术参考。
Numerical optimal design is made on five factors which have effects on total pressure recovery and aerodynamic interface plane circumferential distortion descriptor of an ultra- compact inlet using design- of- experiment. The source term model was added in Navier- Stokes equations instead of microvanes when numerical computation of twenty- seven vortex generator combinations apply in inlet passive control. Based on analysis of results, the best vortex generator combination is presented.
出处
《航空计算技术》
2009年第6期25-29,共5页
Aeronautical Computing Technique
基金
总装备部装计(2006)689号(513130101)
关键词
实验设计
涡流发生器
总压恢复
流场畸变
优化设计
design- of- experiment
vortex generator
total pressure recovery
circumferential distortion descriptor
optimal design
