磁流体流动控制在航空工程中的应用与发展  

Application and Development of Magnetohydrodynamics(MHD) Flow Control in Aeronautic Engineering

作　　者：程邦勤[1] 孙权[1] 苏长兵[1] 李益文[1] 喻永贵[1] 

机构地区：[1]空军工程大学工程学院,陕西西安710038

出　　处：《空军工程大学学报（自然科学版）》2010年第2期11-15,共5页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：国家自然科学基金资助项目(50776100)

摘　　要：总结了国内外磁流体(MHD)流动控制的研究现状,重点介绍了磁流体流动控制的3个典型实验:调节超音速进气道激波系结构,抑制流体边界层分离,减弱诱导激波强度;对磁流体流动控制机理进行了初步分析,说明放电等离子体能在激励区产生高温等离子体层,由于局部气体高温高压诱导出激波,形成虚拟尖劈,从而改变原有流场结构,施加磁场的主要用途是对放电电弧施加宏观的洛仑兹体积力,控制电弧运动的方向。最后,总结了磁流体流动控制的优势,并对国内MHD流动控制在航空工程上的应用与发展进行了展望。The paper summarizes the development of MHD flow control in the world and emphatically introduces three typical experiments： modifying shock wave structure of supersonic inlet; restraining separation of boundary layer; weakening shock wave intensity. The mechanism about MHD flow control is analyzed primarily, i.e. discharge plasma can produce high temperature plasma layer, which will induce new shock wave and become virtual ramp, and thus the former flow filed is changed. The use of applying magnetic field is to control discharge arc direction due to electromagnetic force. Finally, the advantage of MHD flow control is summarized, and according to the comparisons between the foreign and the domestic in research development, the prospect of MHD application and development in aeronautic engineering is performed.

关 键 词：磁流体 流动控制 高超声速 激波 边界层 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]