摘要
为满足超声速二元进气道的气动性能和宽马赫数工作的要求,探索了一种气流角可调式进气道的方案,采用区间搜索优化算法,完成了设计马赫数3.5,起动马赫数2.0的几何可调进气道的最优设计。通过CFD数值结果验证了准确性。结果表明:1与设计值相比,最优设计的几何可调进气道在所有工作马赫数条件下的总体性能均得到较大提升;2通过优化算法估算得到的进气道的性能参数与CFD数值结果相差不大。
A flow angle adjustable supersonic inlet was investigated to satisfy the requirement of aerodynamic performance and operation over a wide range of flight Mach number.An optimal design of variable geometry inlet with range search algorithm at the design Mach number 3.5,starting Mach number 2.0 was conducted.The accuracy was verified by CFD numerical results.Results indicate：① The global performance parameters of the optimal variable geometry inlet are greatly increased in the whole operating range compared with the design value; ② The errors between the predicted performance parameters and CFD numerical results are very small.
出处
《科学技术与工程》
北大核心
2014年第19期135-141,共7页
Science Technology and Engineering
关键词
超声速
几何可调
二元进气道
优化算法
起动
supersonic
variable geometry
two-dimensional inlet
optimization algorithm
starting
