超声速来流下叶片式微型涡流发生器流动控制研究  

Investigation on Flow Control of Supersonic Flow Past Vane Type Micro Vortex Generator

作　　者：王旭东[1] 高峰[1] 徐晨洋 张涵[1] 

机构地区：[1]空军工程大学防空反导学院,西安710051

出　　处：《航空工程进展》2016年第3期273-278,共6页Advances in Aeronautical Science and Engineering

摘　　要：不同构型的微型涡流发生器对提高进气道/隔离段性能所产生的效果不同。采用数值模拟方法研究来流马赫数为2.0条件下,五种叶片式微型涡流发生器对流场边界层的流动控制特性。结果表明:带有一定前缘高度的叶片式微型涡流发生器可产生更强的流向涡,总压畸变和马赫数畸变较小,流场出流质量更佳,但同时带来较大的总压损失;微型涡流发生器的前缘厚度对流场性能提升无明显帮助,反而会增大总压损失;无前缘高度的微型涡流发生器能在引入较小总压损失的情况下,使隔离段拥有较强的抗反压能力,同时有效增大壁面摩擦系数,提高边界层对抗分离的能力。It is proved that different micro vortex generator（MVG） will have different effects to improve the per- formance of the inlet/isolator. The supersonic flow（Ma= 2. O） past vane types of micro-ramps are simulated to improve the characteristics of isolator. Results show that MVG with high leading edge generates stronger s^re- amwise vortex, the total pressure distortion and Mach number distortion decrease but brings higher total pres- sure loss. The leading edge thickness of MVG is not helpful to improve flow control characteristics, but causes more total pressure loss. Flow filed controlled by MVG with thin leading edge will have higher back pressure and increase skin fraction coefficieat.

关 键 词：超声速 隔离段 微型涡流发生器 流动控制 数值仿真 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]