separation vortex 中文意思是什麼

separation vortex 解釋
剝離渦流
  • 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...
  • vortex : n. （pl. vortexes,-ti-ces ）1. 旋渦；旋風；旋卷行雲。2. 【物理學】渦旋；【航空】渦流；【動物；動物學】〈V-〉 單腸渦蟲的一屬。
  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. Although the knowledge of wind effects on tall buildings has significantly improved over the last decades, an understanding of the mechanism that the atmospheric flow field to various wind include effects on structures has not been developed sufficiently for formulation of functional expressions. not only is the wind approaching a building complex, but the flow pattern generated around a building is complicated by the distortion of the mean flow field, the flow separation, the vortex formation, and the wake development

    在過去的幾十年裡，雖然人們對高層建築風效應的了解已有顯著提高，但對大氣流場與結構物各種風致響應的關系還不能用解析表達式加以描述。由於平均流場的奇變、流動分離、旋渦形成以及紊流的發展，不僅使得流向建築物的風，而且使得繞建築物的流譜變得十分復雜。
  3. Wake vortex separation standards are used to prevent hazardous wake vortex encounters which mainly found in the final approach course within the airport termination zone. firstly, this paper analysis the mechanism of the vortex decay and research the influence on the safety of the flight ; then. several different radar wake vortex separation standards are compared and some basic guidelines are developed to establish the future vortex standards. in addition, one kind of advance vortex classification for the civil airplane is proposed. secondly, an encounter hazard model which established for the following aircraft and a simple vortex decay model which mostly concern with the proceeding one are developed ; and a safe separation model can be derived from the both. finally, through the simulation calculation, the correctness of the vortex classification of different types of aircrafts are tested and proved

    本課題對雷達管制條件下的最小尾流間隔標準進行了較為詳細的分析和研究；首先對尾流的形成和消散機理以及尾流對飛行安全的影響做出了詳細的分析，然後就目前實行的幾種不同的最小尾流間隔標準進行了比較和分析，提出了相關的幾條準則和一種改進的機型尾流分類標準；在這之後，採用理論分析和統計數據分析相結合的方法，建立了尾流危險遭遇基本模型和尾渦消散模型；並在此基礎上對民用航空不同機型的尾流分類的合理性進行了計算和評估，為最小尾流間隔標準的確定和改進提供了初步的理論依據。
  4. The computations are shown to agree well with available experimental and numerical data and the physics of 3d large - scale flow separations and vortex shedding are confirmed. the simulation of the flow around a maneuvering wigley hull is a demonstration of capability for calculations of sway forces and yaw moments acting on a hull moving obliquely at a large range of yaw angles. the focus of study is large - scale cross - section separation flows, bilge - vortex development along the hull in the longitudinal direction and their effects on hydrodynamic forces

    應用所開發的求解器，以wigley船型為算例計算了大角度斜航船體粘性流場和水動力，分析了漂角的變化對船體所受到的粘性水動力的影響，相當精確地預報了以橫流分離和般渦生成與泄出為特徵的操縱運動船體特有流動形態及橫向水動力和轉脂力矩，經與現有試驗和計算數據比較，檢驗和驗證了該求解器精確模擬繞斜航運動船體的大尺度分離流動和計算非線性水動力的能力。
  5. In lifting - surface theory, the non - liner phenomena of the trailing vortex in the transition wake area and of the tip vortex separation are considered. in surface panel method hyperboloidal quadrilateral panels are employed and the morino ' s analytical formulation is used to determine the influence coefficients. the more reasonable pressure kutta condition is satisfied at the trailing edge of propeller blade

    在計算中，對于升力面理論，本論文考慮了過渡區尾渦收縮和葉梢分離的非線型現象的影響；對于面元法，本論文採用的是計算較為簡便的基於擾動速度勢的基本公式及雙曲面形狀的面元，在槳葉隨邊滿足更趨合理的壓力kutta條件，並用morino導出的解析公式計算面元的影響系數的快速有效的數值預報方法。
  6. The particle separator ( ips ) is a special device of helicopter used for the purification of the entrance air and the protection of the engine. the vortex blade of the particle separator will be damaged if impacted by the foreign object for a long time, thus the separation efficiency of the particle separator and the safety of the engine will be affected

    粒子分離器是直升機上用來對發動機進行進氣凈化和防護的一種專門裝置，外來物的撞擊會對粒子分離器的渦流葉片造成損傷，影響粒子分離器的分離效率，從而對發動機安全帶來影響。
  7. Three - dimensional gas flow field in the new vortex quick separation system with an inner component of fcc disengager was simulated based on the reynolds stress model ( rsm ) provided by cfx

    摘要用cfx軟體對催化裂化沉降器新型旋流快分器的氣相流場進行了三維模擬，湍流模型採用雷諾應力輸運方程模型。
  8. A mathematical model of flows in the substrate was established using the equivalent continuum approach, and multi - dimensional numerical simulation of the steady flows in the catalytic converters was performed. simulation results show that the separation and vortex, which cause the pressure loss and the velocity non - uniformity at the front of the first substrate, are generated near the wall of the conical pipe. in addition, the larger the inlet cones angle the more the pressure loss and maldistribution in converters, however, when the angle enlarges enough the pressure loss would be decrease

    結果顯示氣流在擴張圓錐管壁附近出現分離產生較強的擾動，造成局部流動損失和載體前氣流速度沿徑向分佈不均勻；入口擴張管結構對催化器的流動特性有很大影響，但並非擴張角越大，催化器流速武漢理工大學碩士學位論文分佈的不均勻性和壓力損失也增大，而是存在著一個最佳角度，但當擴張角增大到一定程度以後，擴張角對流速分佈和壓力損失的影響變小。
  9. Effect of the rectify on the energy separation performance of the vortex tube

    整流器對渦流管能量分離性能影響的研究
  10. 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。
  11. 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。
  12. The performance of energy separation on the vortex tube designed by the author is studied at different cold mass flow ratios, and the characteristic curve has been drawn

    對于本文設計的渦流管，研究了不同冷氣流率時渦流管的能量分離特性，並且繪制了性能曲線。
  13. Experiments have been taken under the conditions of inlet pressure from 0. 25mpa to o. tompa, inlet temperature from 12 ? to 32 ?, and the mass volume flow from om3 / h to 30m3 / h. some valuable results have been obtained through a large quantity of experiments as follows. the inlet temperature of the air has certain influence on the energy separation of vortex tube

    在大量實驗研究的基礎上，證實了在入口壓力0 . 25mpa 0 . 7mpa之間，入口溫度（從12 32之間）對渦流管的冷熱效應有一定的影響，並且隨著入口溫度的升高，渦流管的製冷性能增加，而制熱性能有所降低。
  14. Vortex separation tube

    渦流分離管
  15. In chapter 6, a new idea for simulating rotor bvi noise experiment is presented using a scissors rotor configuration with the vertical separation between a pair of rotors, based upon the fact that the important aerodynamic feature of this scissors rotor configuration is its close blade - vortex encounter. and the models and facilities designed for the bvi noise experiment are given

    在第六章，基於槳-渦靠近通過是非共面剪刀式布置旋翼流場的一個重要特徵，提出了使用剪刀式布置旋翼來模擬旋翼槳-渦干擾噪聲實驗的新構想，並設計了用於噪聲實驗的模型。
  16. 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。
  17. The inlet pressure is one of the important factors for influencing the performance of vortex tube. the separation of hot and cold is not very obvious at pj = 0. 20mpa

    25 k以及一直到060mpa過程中，隨著入口壓力的升高，渦流管能量分離非常顯著；比如，在n 44
分享友人
分享到 Line

分享到臉書