湍流分離 的英文怎麼說

中文拼音 [liúfēnlí]
湍流分離 英文
turbulent separation
  • 湍 : [書面語]Ⅰ形容詞（湍急） rapid; rushing; torrential; swiftⅡ名詞（急流的水） rapids; rushing waters
  • 流 : Ⅰ動1 （液體移動; 流動） flow 2 （移動不定） drift; move; wander 3 （流傳; 傳播） spread 4 （向壞...
  • 分 : 分Ⅰ名詞1. （成分） component 2. （職責和權利的限度） what is within one's duty or rights Ⅱ同 「份」Ⅲ動詞[書面語] （料想） judge
  • 離 : Ⅰ動詞1 （離開） leave; part from; be away from; separate 2 （背離） go against 3 （缺少） dispens...
  • 湍流 : 1 （急流） swift current; rushing waters; torrent; rapids 2 [物理學] turbulent flow; turbulence; ...
  1. In section one, by using fice scheme and time - gcm, a model of trace gases and oh airglow affected by gravity wave is set up, then the propagation of nonlinear gravity wave and the effect on trace gases and oh airglow are analyzed. the result shows gravity wave excited by tropospause forcing can propagate stably to the mesosphere through the stratosphere so that energy and momentum can be transferred from one region to another. in this process, gravity wave undergoes growth, overturning, convection and breaking

    在第一部分的工作中，利用全隱歐拉格式和全球熱層-電離層-中間層-電動力學環流耦合模式（ time - gcm ） ，對重力波的非線性傳播及其在傳播過程中對中高層大氣中氧族和氫族成分和與之密切相關的oh氣輝輻射的影響進行了數值模擬，結果表明，從對流層向上傳播的重力波經歷了產生、發展、飽和、對流產生直至破碎的非線性演化，大氣的非等溫結構加速了重力波在中層頂區的破碎，重力波的非線性傳播是小尺度對流和湍流產生的一個重要的源。
  2. It is showed that numerical calculation could give the same position of separation line with the cold gas simulation. however, numerical simulation result is of a little deferent from cold gas simulation in some details, such as recirculation velocity and turbulent intensity. the main problem of numerical simulation is that the turbulent model is not perfect, and the computational grid is not precise enough

    利用實驗結果對數值模擬的準確性作了檢驗和評價，結果表明數值模擬能給出與實驗結果一致的分離線位置，但在某些流動細節上還有差別，如迴流速度大小和湍流度等，數值模擬中存在的主要問題是湍流模型不夠完善和網格生成不夠精細。
  3. In this thesis, adopting compressible navier - stokes equations and compressible k - - e turbulence double model, studied 2d viscous flow field in wet turbine ' s separate - stage. coordinate transformation is made for the navier - stokes equations by using body fitted coordinate system, moreover, the flow field in 2d cascade is calculated by using the well - established simple method

    本文採用可壓縮氣體的n - s方程，並採用可壓縮的-湍流雙方程模型，研究了飽和汽輪機分離級內二維粘性葉柵流場，採用貼體坐標系對n - s方程進行了坐標變化，並利用成熟的simple演算法對二維葉柵內的流場進行了計算。
  4. For the first time the complex separated flow in the aft - end zone was measured using pdpa technology. the whole mean and fluctuating flow field were obtained

    利用pdpa測速技術首次對燃燒室尾部的復雜分離流動進行了測量，獲得了完整的時均速度和湍流脈動定量數據。
  5. Certain discrepancy remain between the simulation results and the experiment results, not only caused by the turbulent model, but also by the simplification of the inlet boundary condition and the mesh generation. modeling gas - particles interaction flows is complex. in this thesis, gas - phase transport equations coupled with the gas - particle interaction are derived based on the dsm turbulent models to handle the interaction of momentum and kinetic energy of turbulence between the gas and particles

    分離器內的固體顆粒運動採用涉及湍流擴散影響的隨機軌道模型和確定軌道模型，同時在湍流模型中加入了顆粒影響的源項，在流場計算的基礎上，模擬了不同直徑的顆粒在分離器內的運動規律及顆粒分離效率，並同理論和實驗得到的數據進行了比較。
  6. Abstract : approximate methods for calculating aerodynamic heating rates on space shuttles are discussed. various methods are given for predicting the heating rate at axisymmetric stagnation points, general three dimensional stagnationpoints and the leading edge stagnation point of wings. numerous laminar and turbulent heating techniques for flat plates and cones are analyzed and compared. a brief review of some methods is presented to predict heating rate for winward centerline and lateral direction off the symmetry plane. the results show that the methods are simpler and can guarantee enought precision for predicting aerodynamic heating environment of space shuttles

    文摘:介紹了國內外預測航天飛機氣動加熱的工程計算方法.給出了軸對稱、非軸對稱和機翼前緣等各種外形駐點熱流密度的計算，分析和比較了平板、錐體的層流和湍流熱流密度計算的各種方法，概述了航天飛機迎風面中心線和離開中心線橫向熱流密度的計算.計算結果表明，本文方法用在航天飛機氣動熱環境初步設計中比較簡單並且有足夠精度
  7. And then, in the simulation of three - dimensional, the application of o - type grid and hybrid grid are used in two relatively complicated structures make the total amounts of grids and the time of grid generation reduced greatly. moreover the hexahedron grids are placed in most areas to provide higher precision. through the comparison between the results of two - dimensional and three - dimensional simulation, we knew two - dimensional calculating is not adequate

    本文用簡單、方便的二維模型作為數值計算的起點，使用耦合隱式演算法以及先進的v2f湍流模型進行求解，成功地捕捉到了激波，觀察到主氣流從壁面的分離、切換、再附壁等現象，並對計算結果進行了細致的分析，得出一些有意義的結論；在此基礎上，本文在國內外首次對超音速射流雙穩閥的三維流場進行了計算。
  8. To the cabin which is designed by the forth department chongqing communication college, the model which includes the air in the cabin, generator set and public muffler is built integer, meshed, and added by boundary condition and load. the normal k - model etc are used to be turbulence model of the air in cabin respectively, the turbulence model is calculated by simplef or simplen algorithm, and by the first order accurate msu or the second order accurate supg in advection discretization scheme

    論文對艙內空氣、發電機組和公用消聲器進行了整體建模和網格劃分，施加機組艙模型的邊界條件和載荷，採用標準k -等多個模型來分別模擬機組艙通風散熱的空氣湍流流動，採用simplef和simplen兩種不同的數值演算法以及一階msu和二階supg的對流項分離方案來對流動模型進行運算。
  9. 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
  10. In this paper, two - dimensional and three - dimensional flow models in supersonic inlet and a simple reacting flow model in combustor and integrated flow field are established on the basis of k ? two - equation turbulence model and steady - compressible n - s equations, which are dispersed by finite volume method

    本文以定常可壓縮n - s方程作為控制方程，採用-雙方程模型作為湍流模型，分別建立了超聲速進氣道的二維、三維流場計算模型和補燃室及一體化流場的湍流燃燒模型，並採用有限體積法對控制方程進行離散。
  11. The anisotropy invariant map was also introduced briefly. the effect of the distance away from the wall and the reynolds number on the turbulence structure in a pipe flow was also analysed

    介紹了湍流不變量圖在圓管湍流研究中的應用，分析了離壁距離和雷諾數對管流湍流結構的影響。
  12. Flow details of measurement indicate that the coupling of periodic separated flow ( such as low frequency swinging of separation line ) with nozzle flow may cause aft - end internal flow unsteady. recirculation flow gains more energy from the main flow, at the same time the turbulence intensity increases

    通過對測量結果的分析，我們認為分離流動的周期性（如分離線的低頻擺動）與噴管流動相耦合，會造成燃燒室尾部流動的非穩態效應增強，增加了迴流區從主流中獲得的能量，也加劇了流場的湍流脈動。
  13. On the following, on the basis of formulas given above, three kinds of effects due to ionosphere are presented : image shift due to group delay which was caused by the difference between the group velocity and the velocity of light in the ionosphere ; image distortion due to ionospheric dispersion which can create second phase error of lfm signals ; the last, the phase perturbation caused by the irregularities of the ionosphere can reduce the coherent length and affect azimuthal resolution

    文中主要研究了電離層的三種影響：信號經過電離層傳播的群延遲引起的成像偏移；電離層的色散效應給線性調頻信號帶來二次相位誤差，導致圖像退化、失真；以及電離層的閃爍、湍流等不規則性引起的信號相位起伏。在此基礎上，比較分析了不同波段、帶寬條件下電離層的影響。
  14. The turbulence properties of annular space in a cyclone were investigated by using the laser doppler velocimetry

    摘要採用激光多普勒測速系統測試了蝸殼式旋風分離器內的流場，分析了環形空間內的湍流特性。
  15. The improved lagrangian stochastic model has attributed to the successful prediction of the turbulence inhomogeniety, turbulence anisotropy, and particle crossing - trajectories effect. the collisions between the particles are also considered in this thesis. numerical results for the particles trace and collection efficiencies in the cyclone separator were compared with available experimental data and with theoretic models

    為了驗證以上固體顆粒運動模型及修正的湍流模型，文中給出了顆粒在水平管道和u形撞擊式分離器中的運動，比較了不同顆粒軌跡模型的特點及運動行為對流體湍流強度的影響。
  16. 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。
  17. Based on former work, a finite difference viscous code that uses a high convergence, high accuracy, high resolution lu - sgs - ge implicit scheme and an improved fourth ( fifth ) - order high resolution muscl tvd scheme to integrate the full 3d navier - stokes equations and the low - reynolds number two - equation turbulence model is extended to simulate the flow field inside centrifugal impeller mechanism

    並且在現有工作基礎之上，將基於有限差分方法的高收斂率、高精度、高解析度的lu - sgs - ge隱式格式和四（五）階muscltvd格式求解全三維navier - stokes方程和低雷諾數雙方程湍流模型的計算程序推廣到離心葉輪機械內部流場的數值求解。
  18. Numerical simulation on turbulent flow field within liquid - liquid cyclone

    液旋流分離管湍流流場的數值模擬
  19. The method of generating elements and nodes automatically by reading coordinate data on surface of bus body is introduced and realized to discrete the topology space of three - dimensional turbulent flow field around buses

    客車周圍流場三維湍流數值模擬的空間離散化研究實現了由車身外表面離散點坐標數據文件自動剖分生成單元、節點和邊界條件的方法。
  20. Mathematical model and numerical simulation of turbulent for hydrocyclonic separation

    旋流分離的湍流渦動數學模型及數值模擬
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