boundary layer separation 中文意思是什麼

boundary layer separation 解釋
邊界層分離現象
  • boundary : n 邊界,疆界,限界 (between);(球場)邊線;界標;界限,范圍,分野。 aboundary dispute 邊界糾紛...
  • layer : n 1 放置者,鋪設者,計劃者。2 【賽馬】(一般)賭客。3 產卵的雞。4 【軍事】瞄準手。5 層;階層;地...
  • separation : n 1 分離;分類;分開。2 隔開;間隔;脫離。3 (夫婦的)分居。4 分隔物。5 【化學】離析;析出;釋出...
  1. 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 )綜合分析研究了渦流發生器的工作原理和設計原則。根據國內外資料,研究了渦流發生器形狀、高度、展弦比、尖削比、弦向位置、展向位置和方位角等因素對附面層分離控制效果的影響。
  2. The experiment shows that by changing the velocity coefficient, the separation of boundary layer on pump vane can be controlled, and the performance of pump is improved and its hydraulic efficiency

    實驗證明通過改變葉片型線參數方程中的速度系數的取值,可以控制邊界層的分離,進而改善泵的性能,提高其水力效率。
  3. A separation in the boundary layer of fluid about a moving streamlined body, such as the wing of an airplane, causing a breakdown in the smooth flow of fluid and resulting in turbulence

    氣流分離移動的流線型的軀體上流體邊界層上的分隔物,如飛機的機翼,在平滑的流體流動中會引起故障和湍流
  4. According to the comparison between simulation results and laboratory measurements, this paper reaches the conclusion that the negative pressure region in convex boundary ( including broken line gradient ) not only caused by boundary layer separation, but also especially caused by centrifugal force which is the result of convex boundary

    根據數值計算與模型試驗結果的比較,得出具有凸形曲面邊界(包括折面底坡)負壓區的存在不僅是邊界層分離所致,邊壁彎曲使過流產生的離心力也是產生負壓的重要原因的結論。
  5. Firstly, based on n - s equation, the momentum differential equation ( contained centrifugal force ) is derived by simplification in boundary layer and then integrates the differential equation over the thickness of the boundary layer, the momentum integral equation is deduced. the dimensionless centrifugal factor is introduced, then the solution of the momentum integral equation is obtained. the dimensionless group is introduced to determined separation of boundary layer

    本文首先根據粘性流體力學的一般方程,通過在邊界層內進行量級比較,在所限定的范圍內得到了含有離心力的邊界層動量微分方程並給出其滿足的邊界條件,然後對該微分方程在邊界層內積分得到離心泵葉輪邊界層動量積分方程,在求解過程中引入了無量綱離心因子,並作了相應合理的假設,得出積分方程解的一般表達式,並引入以邊界層動量損失厚度為主要特徵量的無量綱參數對邊界層分離進行評價。
  6. The micro shear stress sensor which based on the smart skin for boundary - layer separation point detection of delta wing has been explored in this paper

    本文就以用於實現三角翼邊界層分離點檢測的面向靈巧蒙皮的微型剪應力傳感器為對象展開研究。
  7. According to the theory of boundary layer and the important of boundary - layer separation point detection of delta wing, the measuring principle and structure scheme of various system alternatives based on mems technology have been discussed, selecting the prototype of better workability. base on the master piece model of micro shear stress sensor

    首先,結合空氣動力學的邊界層原理,針對三角翼邊界層分離點檢測在實現主動氣動控制方面的重要性,討論了光學式、電容式和熱敏式微型剪應力傳感器的測量原理和結構方案,選取適合加工條件的微型剪應力傳感器樣件。
  8. 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

    給出了該翼型的附面層特性:翼型表面基本為湍流附面層;在靠近附面層分離位置處,速度型形狀、特別是靠近翼型表面的底部速度型形狀變化不定,是湍流流動的隨機性所致;該翼型具有較好的附面層分離形態,但在失速迎角附近,附面層分離形態變化劇烈、失速特性差,是翼型上翼面形狀較為平坦所致。
  9. 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,從控制該翼型附面層分離、提高大迎角氣動性能的角度出發,通過風洞實驗研究,研究了該翼型的附面層特性和氣動性能,針對其附面層特性,給出了梯形、三角形和翼型式三種渦流發生器設計方案,為下一步研究工作奠定了堅實基礎。
  10. 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

    近十年來,用於飛機機翼附面層分離控制的渦流發生器發展很快,出現了亞附面層、微型和智能化渦流發生器等新概念。
  11. 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

    用該程序分別計算了nasa - 37跨音速轉子和nwpu - 1亞音速轉子,計算結果表明本文建立的孤立轉子程序能夠較好的模擬軸流壓氣機葉片排內流動情況,能夠有效的捕捉通道激波和間隙泄漏渦軌跡以及葉片附面層的分離。
  12. Results from this investigation show that the loss generation within the coolant holes is substantial and that ejection into regions of low static pressure increases the loss per unit coolant mass flow. the results also reveal strong interactions between endwall coolant ejection and secondary flow in the blade passage. the secondary flow has a strong influence on coolant trajectories and coolant ejection delays the three - dimensional separation of the inlet boundary layer on the endwall, chang the secondary flow and reduces its associated losses

    本文的研究成果顯示,冷卻孔內產生的損失是主要的,並且低靜壓區域的冷空氣噴射會增加單位冷空氣質量流的消耗;噴射的冷空氣與葉柵端壁流場之間有強烈的相互作用;二次流對冷卻空氣的流動軌跡有較強的影響;冷空氣噴射能延緩端壁入口邊界層的三維分離、改變二次流從而減少其相關損耗。
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