附面层分离的英文

• boundary layer breakaway
• burbling

• "分离"英文翻译    separate; sever; resolve; se ...
• "附面层分离的检定" 英文翻译 :    detection of boundary-layer separation
• "附面层分流板" 英文翻译 :    boundary-layer splitterpiston
• "分离的附面层" 英文翻译 :    separated boundary layer
• "无分离的附面层" 英文翻译 :    intact boundary layer
• "附面层" 英文翻译 :    blanket; boundary-layer flow; frictional boundary layer
• "激波引起分离的附面层" 英文翻译 :    shock-separated boundary layer
• "壁附面层" 英文翻译 :    wall layer
• "边界层；附面层" 英文翻译 :    boundary layer
• "弹性附面层" 英文翻译 :    compliant coating
• "低能附面层" 英文翻译 :    slow boundary layer
• "低速附面层" 英文翻译 :    lower-speed boundary layer
• "低阻附面层" 英文翻译 :    low-drag boundary layer
• "地面附面层" 英文翻译 :    ground boundary layer
• "定常附面层" 英文翻译 :    constant property boundary layer
• "定态附面层" 英文翻译 :    steady-state boundary layer
• "定压附面层" 英文翻译 :    constant-pressure boundary layer
• "冻结附面层" 英文翻译 :    frozen boundary layer
• "洞壁附面层" 英文翻译 :    tunnel-wall boundary layer
• "多相附面层" 英文翻译 :    multiphase boundary layer
• "二维附面层" 英文翻译 :    two-dimensional boundary layer
• "附面层边界" 英文翻译 :    boundary layer edge
• "附面层表面" 英文翻译 :    boundary layer seam
• "附面层测量" 英文翻译 :    boundary layer measurement; boundary layer survey
• "附面层常数" 英文翻译 :    boundary layer constant

• In recent decades , vortex generators used in separation control on wing boundary layer have developed rapidly . some new conceptions such as sub boundary layer , micro & intelligent vortex generators are coming up
  近十年来，用于飞机机翼附面层分离控制的涡流发生器发展很快，出现了亚附面层、微型和智能化涡流发生器等新概念。
• Finally , the two dimensional flow in the diffuser is calculated , the results show that the change of ma makes an effect to the performance of the diffuser . owing to the accretion of ma , the action of oblique shock waves and the boundary layer pricks up , the flow separates from the wall where the shock waves impinge on the boundary layer more quickly , the cluster of diamond shock waves becomes larger . moreover , by comparing the change of flow field under different structure parameter , it is found that the augment of length of constant area section alter the structure of fluid field little , a smaller area ratio and larger angle of compression section make the diffuser working better
  最后,针对扩压器中的二维流场进行了数值模拟,结果表明马赫数对扩压器性能影响较大,随着马赫数的增大,扩压器管道内激波-附面层干扰加剧,流动从附面层分离相应加剧,激波串数目增多;通过比较不同结构参数下的扩压器内流场,发现等直段长度的变化几乎没有改变流场结构,只是对局部流场稍有影响,并且在其它参数不变的情况下,一定范围内减小面积比a2 / a1和增大收缩角有利于扩压器性能的提高。
• 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。
• 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。