flow on wing 中文意思是什麼

flow on wing 解釋
機翼繞流
  • flow : vi 1 流，流動。2 （血液等）流通，循環。3 流過；川流不息；（時間）飛逝；（言語等）流暢。4 （衣服、...
  • on : adv 1 〈接觸、覆蓋〉上去；開（opp off）。 turn on the light [radio water gas] 開電燈[收音機、自來...
  • wing : n 1 翼，翅膀；鳥；鳥群；飛行，飛翔。2 （飛機）機翼；翼狀物；（汽車的）擋泥板；〈詩常 pl 〉船帆。3...
  1. 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。
  2. Experimental investigation on unsteady flow fieldabout a coupled pitching - rolling delta wing

    滾擺耦合復雜流場試驗研究
  3. This paper has mainly made a research on the aerodynamic configuration design of " w " tailless aircraft and the design idea has been presented here. according to the configuration design requirement of certain uav, aerodynamic configuration design has been carried out and two configuration projects are given out at last : forward - swept wing tailless configuration and " w " tailless configuration. the longitudinal and lateral aerodynamic characteristics are obtained by using two aided soft : ug to build up geometrical models and mgaero to calculate flow field

    本文研究了「 w 」型無尾布局的氣動外形設計，闡述了該布局的氣動設計思想，根據型無人機的總體設計技術指標，進行了氣動外形設計，提出了兩種氣動布局方案：前掠翼無尾氣動布局和「 w 」型無尾氣動布局，利用ug建模軟體和mgaero氣動分析計算軟體計算了兩種布局的縱、橫向氣動性能，分析了前掠翼前緣掠角和翼身融合對氣動性能的影響，計算結果表明， 「 w 」型氣動布局的設計思想是正確的，所設計的「 w 」型無尾氣動布局方案的氣動性能優越，超過了總體設計技術指標。
  4. Many test cases are calculated to verify the above study. the cases are either real or standard testing models, including multi - element airfoil, wing - body configuration, cone / cylinder missile model and 3 - d high - lift systems, etc. the results of present calculation are in good agreement with experiment data, and show flexibility and accuracy of the approaches. base on the cartesian grids, this thesis has targeted the development and integration of many algorithms and techniques such as adaptive refinement, omni - tree data structure, hybrid grid method, etc. an analysis software and research methods are designed and developed for the steady - unsteady and viscous - inviscid flow complex systems and configuration

    7 .運用上述研究成果和結論，進行了大量算例的實驗驗證，外形范圍包括多種標模與型號，涉及多段翼型、 m6機翼、細長體模型、翼身組合體、兩段機翼增升標模、帶縫翼和襟翼的三段增升翼身組合體等復雜外形，計算結果均與實驗吻合良好，充分說明了本文發展的各種演算法、流場求解、網格生成方法的正確性和魯棒性。
  5. Quantitative flow visualization on unsteady flow fields of wing rock

    滾擺非定常流場的定量流動顯示
  6. In order to predict hydrodynamic characteristics a computational system is developed including determination of the pressure distribution on a wing section by use of the conformal mapping method and panel method respectively and of the flow in boundary layer according to the thin shear layer approximation ( tsl ) for navier - stokes equation approach. the wing sections of naca4412 and naca0012 are applied to test the computational system. the numerical inspection shows that the panel method with better precision and the momentum and the displacement thickness of boundary layer can be used to complete this calculation

    本文分別用守屋的保角變換法和基於源匯渦分佈的面元法，建立了計算槳葉表面壓力分佈的數學模型；應用納維-斯托克方程的薄層近似理論模式和有限差分數值方法，建立了計算機翼表面邊界層內部流動的數學模型；應用槳葉表面邊界層內部粘性流動和外部勢流流動在邊界上的匹配演算法，建立了槳葉表面二相流流動的計算方法和相應的計算機程序。
  7. Through solving the unsteady flow fields of an airfoil - flap, the mechanism of buzz is intensively studied. on the basis of the unsteady flow fields of an airfoil - flap with an upper - wing spoiler, the mechanism of the upper - wing spoiler suppressing the buzz is researched. in additions, the comparisons of the unsteady flow fields of an airfoil - flap with and without a separator show that the separator reduce the speed of the buzz

    從非定常流場計算出發系統的研究了嗡鳴發生的機理以及擾流片對嗡鳴起抑制作用的機理；應用能量法確定了嗡鳴發生的邊界；並且研究了機翼舵面之間有隔膜和無隔膜以及機翼上有上翼擾流片和無上翼擾流片對嗡鳴發生邊界的影響；得出了有意義的結論。
  8. This method makes it possible for investigating the unsteady nonlinear potential flow in a complicated environment with higher efficiency. the aerodynamic forces of a wing in couple motion of heave and pitch with ground effect are analyzed in detail based on the numerical result. it is shown that a thrust force exists when the wing is in heave motion

    深入系統地分析了存在表面效應時機翼運動規律和氣動力之間的關系，研究結果表明，機翼升沉運動產生的推力與升沉速度幅值的平方成比例，推力和推進效率和振蕩頻率成反比；機翼的俯仰運動可以調節推力和推進效率，但是單純的俯仰運動不會產生推力。
  9. Utilizing the disturbance of micro - flow to realize the control on the main flow is an important method of flow control, especially for adaptive wing boundary layer control

    利用微流場的擾動來實現對主流場的控制一直是流場控制的一種重要方法，尤其是在對自適應機翼的邊緣層控制中。
  10. Experimental studies on leading - edge vortex breakdown and control of flow over 76 176 ; 40 176 ; double delta wing

    雙三角翼前緣渦破裂及其控制實驗研究
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