湍流模式 的英文怎麼說

中文拼音 [liúmóshì]
湍流模式 英文
turbulent model
  • 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...
  • 模 : 模名詞1. （模子） mould; pattern; matrix 2. （姓氏） a surname
  • 式 : 名詞1 （樣式） type; style 2 （格式） pattern; form 3 （儀式; 典禮） ceremony; ritual 4 （自然科...
  • 湍流 : 1 （急流） swift current; rushing waters; torrent; rapids 2 [物理學] turbulent flow; turbulence; ...
  • 模式 : model; mode; pattern; type; schema
  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. Computation of three - dimensional unsteady periodical turbulent flow though a draft tube

    尾水管動態計算湍流模式的選擇
  3. Study of numerical method for flow transition prediction based on turbulence model

    一種基於湍流模式的轉捩預測方法
  4. 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。
  5. Based on theoretical analysis, microbubble drag reduction is due to structure change of turbulent boundary layer caused by the microbubbles. experiments testify microbubble drag reduction for turbulent boundary layer, as well as bubble size, main flow velocity, etc. affecting the reduction ; with proper flow field model, turbulent model and difference scheme, numerical methods simulate the effect of boundary layer and bubble numbers on dray reduction

    理論分析提出微氣泡降阻機理在於其引起湍流邊界層結構的變化；實驗證明了微氣泡對湍流邊界層的降阻作用以及氣泡尺度、主流速度等對降阻作用的影響；數值方法利用適當的流場模型、湍流模型和差分格式，模擬邊界層和氣泡數等對降阻的影響。
  6. Nonlinear turbulence models in shock boundary - layer interaction

    邊界層相互作用的非線性湍流模式
  7. Overview of turbulent models

    湍流模式理論綜述
  8. Recently in the simulation of indoor airflow, mainly adopted is the turbulence model theory, rans, which solves only the time - averaged flow field and cannot reveal the characteristics of the rapidly changing of turbulence

    目前室內氣流模擬主要採用湍流模式理論（ rans ） ，但該方法求解的是時均場，體現不了湍流場瞬息萬變的特點。
  9. To prove the accuracy of the mach number, and the parameter homogeneity of the design nozzle " s exit, cfd calculate has carried on the design results. under the condition of supersonic and hypersonic flow, and a certain range of temperature, and mach number, the conclusion of the influence of specific heat to nozzle design is drawn

    為了驗證所設計的噴管出口馬赫數的大小和噴管出口流場的均勻性，採用nnd格式和b l湍流模型求解雷諾平均n - s方程，對設計結果進行了cfd驗算，得出了在一定溫度范圍內，超音速、高超聲速流動的條件下，不同馬赫數范圍內變比熱容對噴管型面和噴管出口馬赫數的影響。
  10. In this paper, maccormack explicit time - split scheme, baldwin - lomax algebraic turbulent model and two - steps hydrogen - air nonequilibrium chemical kinetics model are employed to simulate the 2 - d flow fields in a fixed geometry scramjet combustor in different injecting way of fuel in different flight conditions. the results show, in the same entrance condition, the operating mode of scramjet combustor is influenced by the control of fuel

    本文採用maccormack顯式時間分裂法、 b - l代數渦粘性湍流模型及氫-空氣兩步非平衡化學動力學反應模型，模擬了在不同的飛行馬赫數條件下，固定幾何的雙模態燃燒室在不同供油規律下的二維燃燒流場。
  11. 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。
  12. In consideration of computation exactness and cost, the unstructured grid, rng k - e turbulence model, renold - averaged n - s equations and second order upwind scheme were used to solve 3d turbulence flows with and without secondary combustion of a experimental strutjet rbcc in ejecting mode

    在綜合權衡精度和速度的基礎上選取非結構網格技術、 rngk -湍流模型、雷諾平均n ? s方程、二階上風顯式離散格式求解並研究了支板式rbcc引射模態三維燃燒流場。
  13. 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。
  14. Governing equations of a modified k - model is derived in a three - dimensional cylindrical polar coordinate system, and an available equation is produced

    首先給出單相螺旋流流場在三維圓柱坐標下的修正-湍流模型的控制方程，得出控制方程組的通用形式。
  15. Scramjet inlet is of great importance in the hypersonic airbreathing propulsion system and plays significant role in the realization of hypersonic flight. full 3 - dimensinal n - s equations are solved by using finite volume method, second - order harten - tvd spatial scheme, and algebraic baldwin - lomax turbulence model

    本文基於favre質量加權平均的三維navier - stokes方程，採用有限體積法、二階的tvd格式進行流場求解，並使用了bladwin - lomax代數湍流模型。
  16. In this paper, a three - dimensional ( 3d ) program for the three - dimensional reactive flow fields of complicated geometric nozzle, which governed by the compressible full navier - stokes equations with realizable k - s turbulent model, has been upbuilt by using full implicit couple arithmetic and fvm ( finite volume method ) based on understanding and assimilation of a two - dimensional program group of cr ( chamber - radon ). the new program fulfils the urgent need of numerical tools for simulating three - dimensional reactive flow - fields of hylte ( hypersonic low temperature ) and other latest nozzles, for which cr is out of action in simulation, and can be applied to simulate other chemical laser system, such as chemical oxygen iodine laser ( coil ), overtone fluoride hydrogen, all - gas iodine laser, and so on. furthermore, some related topics about nozzles design and engineer ing also have been discussed

    本文在二維cr （ chamber ? radon ）程序研究的基礎上，採用有限體積方法和完全隱式的耦合演算法，通過求解帶realizablek -兩方程湍流模型的多組分、有反應的三維完全納維埃?斯托克斯（ n ? s ）控制方程，建立了一套能夠對復雜形狀的三維噴管和光腔進行數值模擬的三維程序，解決了連續波df hf化學激光器增益發生器設計缺乏三維數值模擬工具的問題，並用該工具解決了cr程序無法實現的hylte等復雜三維噴管流場的理論模擬問題。
  17. There is only such report on the idi diesel engine by foreign countries according to my materials. 4. firstly finished the improved curl model and combined with the turbulent model to set up a spray and combustive stochastic model of di diesel engine, using monte carlo method to simulate it

    針對直噴式柴油機的特點，在國內首次完成了利用改進的curl碰撞?離散模型，並結合湍流模型建立了直噴式柴油機噴霧和燃燒的隨機模型，並利用montecarlo法進行數值求解。
  18. Numerical investigation of three - dimensional steady jet - interaction phenomenology. ( 1 ) aerodynamics characteristic is calculated by using renolds - averaged navier - stokes equations discretitted in cell - centered finite volume framework and improved on baldwin - lomax turbulent model for the slender body at the high angle of attack

    （ 1 ）採用三維積分形式n - s方程的中心有限體積離散方法，提出了改進的b - l湍流模型，進行了較大攻角彈體的氣動特性計算和結果分析。
  19. The moving grid of type c - h for wing are generated by an algebraic procedure. the steady and unsteady transonic ( and subsonic ) viscous flows around wing are numerically simulated. the 3 - dimensional time - averaged compressible navier - stokes equations with b - l or j - k turbulent models are solved by the implicit lu - n7nd algorithm

    用代數方法生成機翼的c - h型運動網格，從三維非定常n - s方程組出發，利用lu - nnd有限差分格式和b - l或j - k湍流模型建立了一種數值模擬三維機翼的亞、跨、超音速定常及非定常粘性繞流的方法和程序。
  20. This method has different consideration with conventional ways, it can reduce the disposal time for almost 100 times, and resolve the efficiency problem successfully. with the help of research in this paper, the capability of using overlap grid has been improved greatly and many old work based on structural - grid, such as difference scheme, turbulence model, can be used in moving - grid field of overlap grid technology and expand our research field for cfd remarkably

    通過本文的研究，使我們應用重疊網格處理復雜外形的能力得到顯著提升並使我們基於結構網格做的許多研究工作，如各種差分格式以及各種湍流模型的比較研究、大攻角問題等專項研究平滑地過渡到基於重疊網格的動網格應用領域來，較大地拓展了我們的研究應用領域。
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