附面层

• Although a dual - mode scramjet ' s configuration is simple and mainly consists of inlet , combustor and wake nozzle , its working process is complicated , especially in the combustor , involving a lot of subjects , including hypersonic aerodynamics , combustion chemistry , etc . the inner flow of a combustor is three - dimensional and complicated , including the interaction of shock wave , deflagration , vortex and boundary layer , and so on
  它涉及到高超声速空气动力学、燃烧化学、扩散传质等多门学科；其内部的实际流动是复杂的三维流动过程，充满着激波、膨胀波、燃烧波、各种涡系、附面层及其相互之间的干扰，因此，燃烧室问题是整个发动机研究的关键所在。
• The velocity distributions , the relative mach number distributions and the flow trace distributions are visualized , and the reasons , which cause bad aerodynamic losses and make the flowfield complicated , are analyzed , including wake , secondary flow , separated flow and the interaction between shock and boundary layer
  显示压气机内的速度场、相对马赫数分布及流动迹线分布等，并分析造成严重损失及使流场趋于复杂紊乱的原因，包括尾迹、二次流、分离流及激波/附面层干扰等现象。
• The vortex simulated in this article include the shedding vortex induced by the vane trailing edge boundary layer , the endwall vortex generated by the endwall boundary layer interaction , the passage vortex generated by the rotor rotation , and the leakage vortex generated by the tip clearance flow
  涡轮级内的涡运动包括：导向器叶片尾缘附而层引起的脱落涡；转子通道内转子的旋转运动产生的通道涡；根脚区两个端壁附面层干涉，形成的根脚涡；存在叶尖漏流时，出现的漏流涡。
• Nasa - 37 transonic and nwpu - 1 subsonic rotors are calculated by using this program . results of calculation indicates that this program can admirably simulate rotor rows flow in axial compressors and distinguish passage shock , leakage vortex path and separation of boundary layer
  用该程序分别计算了nasa - 37跨音速转子和nwpu - 1亚音速转子，计算结果表明本文建立的孤立转子程序能够较好的模拟轴流压气机叶片排内流动情况，能够有效的捕捉通道激波和间隙泄漏涡轨迹以及叶片附面层的分离。
• 3 . the characteristics of boundary layer ' s transition , shape and separation are researched . the details as follows : ( l ) airfoil surface is turbulent boundary layer flows ; ( 2 ) velocity figure changed unsteady near the point of boundary layer separation due to randomicity of turbulent flow ; ( 3 ) the airfoil have better state of boundary layer separation and poor stall characteristics because of the upper surface of airfoil is flat
  给出了该翼型的附面层特性：翼型表面基本为湍流附面层；在靠近附面层分离位置处，速度型形状、特别是靠近翼型表面的底部速度型形状变化不定，是湍流流动的随机性所致；该翼型具有较好的附面层分离形态，但在失速迎角附近，附面层分离形态变化剧烈、失速特性差，是翼型上翼面形状较为平坦所致。
• In this paper , the boundary layer characteristics of a supercritical airfoil is researched in wind tunnel . from the start to control boundary layer separation and to improve aerodynamics characteristics of this airfoil , three kinds of trapezoid , delta and airfoil shaped vortex generators are designed based on traditional , sub boundary layer and micro - vortex generators conceptual design . it include as follows : 1
  研究工作中，从控制该翼型附面层分离、提高大迎角气动性能的角度出发，通过风洞实验研究，研究了该翼型的附面层特性和气动性能，针对其附面层特性，给出了梯形、三角形和翼型式三种涡流发生器设计方案，为下一步研究工作奠定了坚实基础。
• The results indicated that the generation of trailing - vortex of downstream adjacent vanes could be restrained effectively by upstream wake when the passing frequency and the amplitude of wake defect satisfy some conditions , associated with a significant enhancement of time - averaged aerodynamic performances : loss coefficient reducing 40 . 2 % and the ratio of loading coefficient and loss coefficient increasing 93 %
  研究表明：满足一定通过频率和亏损幅值条件的尾迹能够有效抑制下游相邻叶排尾缘涡的生成，达到控制或是推迟附面层非定常分离的目的，从而使得流场时均性能大幅度的提高，损失系数降低了40 . 2 % ，功损比增加93 % 。
• Three kinds of trapezoid , delta and airfoil shaped vortex generators are designed based on traditional , sub boundary layer and micro - vortex generators conceptual design , to study the influence of the shape , height , aspect ratio , chordwise position , spanwise position and direction angles of vortex generators on boundary layer separation control
  ( 5 )综合分析研究了涡流发生器的工作原理和设计原则。根据国内外资料，研究了涡流发生器形状、高度、展弦比、尖削比、弦向位置、展向位置和方位角等因素对附面层分离控制效果的影响。