非定常 的英文怎麼說

中文拼音 [fēidìngcháng]
非定常 英文
nonstationary
  • 非 : Ⅰ名詞1 （錯誤） mistake; wrong; errors 2 （指非洲） short for africa 3 （姓氏） a surname Ⅱ動詞1 ...
  • 定 : Ⅰ形容詞1 （平靜; 穩定） calm; stable 2 （已經確定的; 不改變的） fixed; settled; established Ⅱ動詞...
  1. The stability of the tiltrotor in the heli copter mode is analyzed aiming t a semi span soft - inplane tiltrotor model with an elastic wing

    集成了非定常動態人流方程與傾轉過渡狀態的多體動力學力程，建立了傾轉旋翼機時域非定常氣彈耦合分析模型。
  2. A method for calculating transient temperature in helical gears

    斜齒輪非定常溫度場的計算
  3. In this paper, a crank - nicolson mixed element method, a nonlinear galerkin mixed element method for the non stationary conduction - convection problems time second order accuracy fully discrete formats and a two - level mixed element method with backtracing for the stationary conduction - convection problems are presented and analyed, respectively, an error analysis are provided for the crank - nicolson method of time discretization applied to spatially discrete galerkin mixed element approximations of the nonstationary conduction - convection problems

    本文分別給出了非定常的熱傳導-對流問題的crank - nicolson混合元法時間二階精度全離散格式，非線性galerkin混合元法時間二階精度全離散格式以及定常的熱傳導-對流問題回溯二重水平法。討論了時間上的crank - nicolson離散方法應用於非定常的熱傳導-對流問題的空間離散的galerkin混合元近似。
  4. In order to verify the accuracy, credence and effectiveness of the unstructured overset grid algorithm, steady and unsteady flow field of naca0012 airfoil are simulated. the unsteady flow field is caused by the oscillation of the airfoil. the two computational results are both compatible well with the experimental data

    為了驗證非結構重疊網格方法的正確性、可靠性和有效性，本文對基於非結構重疊網格的naca0012翼型的定常流場以及簡諧振蕩的非定常流場進行了數值模擬，均取得了與實驗數據符合良好的結果。
  5. The wing is modeled structurally by vibrational modes, which are used as amplitude of motion by a finite element analysis. conservative full - potential equation and three dimensional unsteady euler equation are used to compute the unsteady transonic flows around airfoil and wings under simple harmonic motion

    以給定機翼模態分佈下機翼上各點的模態值作為運動幅值，以三維非定常全位勢方程和三維非定常euler方程為控制方程，求解三維機翼簡諧運動下的非定常氣動力。
  6. A mathematical model reflecting the tilt rotor unsteady and nonlinear aerodynamic characteristics in the longitudinal channel is presented in the paper. in the full flight envelope, the rotor thrust continues tilting and the aerodynamic forces of each component change as a function of airspeed and nacelle angle

    在整個飛行包線內，旋翼的推力矢量方向不斷變化，飛機各部件的氣動力隨發動機短艙傾角和空速的變化而變化，因而飛機的飛行動力學有很強的非定常、非線性特性。
  7. The transonic steady / unsteady navier - stokes / euler flow solvers based on ausm + scheme have been developed in this dissertation. the structured grids are generated using transfinite interpolation. a cell - centered finite volume approach is used

    因此，研究開發高效、高精度、高魯棒性、實用的跨音速定常、非定常navier - stokes euler方程解算器至關重要。
  8. Uncoupling method in unsteady transport problems across the wall of the network of permeable tubes

    可滲透管網路非定常跨壁傳輸問題的解耦演算法
  9. The viscid flux is discretized by second - order central difference scheme. baldwin - lomax turbulence model is implemented in navier - stokes flow solver. for steady - state calculations, a four - stage runge - kutta scheme with convergence acceleration techniques such as local - time stepping and implicit residual smoothing is used

    其中，定常計算中的時間推進採用四步runge ? kutta方法，並應用了當地時間步長、隱式殘值光順等加速收斂措施；非定常計算中的時間推進採用jameson的隱式雙時間方法。
  10. So the model is more integral and accurate in describing the performance of heat and mass transfer in the adsorbent bed than the traditional mathematical model. 4. pens ( perturbational exponential numerical scheme ) is adopted to ensure the successful solving of the mathematical model and the reliability of results

    採用攝動精確數值解格式（ pens ）來求解數學模型中的主要控制方程，並且考慮到控制方程的非定常性，對原pens格式進行了非定常變換，保證了數學模型計算的成功和結果的可靠性。
  11. On the base of the numerical simulation of unsteady viscous flows, the characters of the static aeroelastics and flutter for the wings are researched. some examples, simulating the steady and unsteady transonic ( and subsonic ) viscous flows around onera m6 wing, are given in this paper

    以oneram6機翼為算例，分別對其亞、跨音速定常及非定常粘性繞流狀態進行了數值模擬，並運用b - l和j - k兩種湍流模型計算結果和實驗數據進行了對比。
  12. Firstly, a representative wind and wave model, which could both simulate the main characteristics of wig over sea waves and be suitable for numerical calculation, is presented. the model completely considers the fully nonlinear effect of wave surface on the wavy air flow, separates the disturbance of wave surface from the wing - air wave interaction flow, and overcomes the numerical calculation difficulties due to the large difference of dimensions between wing and water waves

    首先針對機翼在風浪中的非定常非線性氣動力問題，提出了一個既能夠反映風浪場主要特徵又適合於數值計算的風浪場模型，該模型完整地考慮了波浪表面對氣流場的全非線性影響，使波面對流場的擾動分離出來，消除了機翼和波浪幾何尺度上的巨大差異帶來的數值計算上的困難。
  13. The fundamental ideas and methods of this paper are also illuminated in this chapter. in chapter two, a one - dimensional and semi - closed shallow sea mode is studied. the approximate analytical expressions of the water level at the top of the bay induced by the nonlinear interaction between the storm surges and the astronomical tides are obtained by using the perturbation method

    在第二章里，研究了一維半封閉水域中的非定常風暴潮與天文潮非線性相互作用的問題，用攝動方法求出了具有實際意義的海灣頂部增水水位的一階近似解析表達式，並給出了增水過程曲線。
  14. Study of crossflow topology of unsteady vortex motion over a delta wing

    三角翼非定常旋渦運動橫截面拓撲結構研究
  15. It is necessary to study the unsteady nonlinear aerodynamic characteristics of a wig flying in air with disturbed waves for the design of high - performance wig vehicle, especially for the subject that how to improve the safety, maneuver ability near sea wave, and economics of the wig flying over sea waves

    研究地效翼在風浪擾動氣流場中掠海飛行的非定常氣動力問題，對于高性能地效翼船的設計，特別是對于提高地效翼船在風浪中飛行的安全性，操縱性以及經濟性都是十分重要的。
  16. Numerical investigations of the effects of different leading - edge profiles on the vortex flows over double - delta wings

    繞三角翼流動中的非定常現象研究
  17. Based on an engineering background, through numerical simulation of the flow field in the hp turbine of the energy efficient engine ( e3 ), the article research the unsteady flow in a transonic turbine stage, the unsteady phenomena in the stage include the shockwave, wake, shedding vortex, endwall vortex, passage vortex and leakage vortex, etc. there are two shockwaves generated on the vane the tailing edge, one on suction side is named moving shockwave, and name another on pressure side steady shockwave

    本文首先對于研究的意義和國內外研究的現狀做了簡要的介紹，再從某工程背景出發，通過對e3發動機高壓渦輪內流場的數值模擬，研究了干涉的周期性的問題，以及渦輪級內常見的非定常現象：激波、尾跡、脫落渦、根腳渦、通道渦、漏流渦。導向器尾緣會出現兩道激波，在吸力面的激波可稱為「運動」激波，壓力面的激波可稱為「定常」激波。
  18. Enhanced unsteady and nonlinear rotor wake model for real - time flight simulation

    一種適合飛行模擬應用的非定常非線性旋翼尾跡增強模型
  19. Fluid abnormal motion

    液體非定常流動
  20. As to the current problems existing in the identification for these flutter derivatives, the dissertation tries to trace the development in the identification for the past unsteady aerodynamic forces of long - span bridges. it also investigates the method for flutter and buffeting analysis and the flutter derivatives. based on the present methods used in obtaining the unsteady aerodynamic forces and flutter derivatives, and co - funded by a natural scientific fund from the nation and a key project fund from the railway ministry, the current research has attempted to develop a device which can be employed in the wind tunnel to test flutter derivative through a forced vibration method

    鑒于目前橋梁斷面顫振導數識別的水平和存在的問題，本文通過對大跨度橋梁非定常氣動力、顫振分析方法及顫振導數識別方法的回顧和評述，基於現有的非定常氣動力和顫振導數的測試方法，在國家自然科學基金與鐵道部重點學科基金的聯合資助下，研究開發了一套在風洞中採用強迫振動法測試顫振導數的裝置。
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