wing equation 中文意思是什麼

wing equation 解釋
機翼理論方程
  • 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...
  • equation : n. 1. 平衡，均衡；平均，相等。2. 【數學】方程式，等式。3. 【天文學】（時）差；均分，等分。4. 【化學】反應式。
  1. 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。
  2. The interior temperature distribution and ablation model of projectile wing is established from general transmitting heat differential equation ; at the same time, the heat flow density and pressure distribution model of projectile wing is also established

    從一般形式的導熱微分方程出發，逐步建立了彈翼內部溫度分佈和燒蝕的數學計算模型；與此同時，建立了彈翼表面的熱流密度和壓力分佈的數學模型。
  3. 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。
  4. Moreover, in the application of aircraft structures design, the composite wing is still to meet the needs of aeroelastic design. through reading the aerodynamic influence coefficient matrix from the nastran file, this paper generates a static aeroelastic equilibrium equation and divergence eigen - equation, which is needed by the aeroelastic tailoring of composite wing. through this equation, the aeroelastic tailoring of composite wing and its optimization design have come into being

    此外在飛機結構設計過程中，復合材料翼面結構還要滿足氣動彈性設計的需要，本文通過讀入由nastran所產生的氣動影響系數矩陣，構造出滿足復合材料氣動彈性分析所需要的靜氣動彈性平衡方程和發散特徵方程，並在此基礎上實現了復合材料氣動彈性剪裁優化設計。
  5. The effective optimization design programs for different cases are developed by integrating the following several aspects which involves the flow analysis, adjoint equation solution, gradient solution, optimal arithmetic and grid generation. some practical design tests for airfoil and wing show that the continuous adjoint approach is very effective and useful method for aerodynamic optimization design. at the same time, we have done the research of aerodynamic optimum design for airfoils by using navier - stokes equations

    （ 4 ）研究了基於控制理論和三維navier一stokes方程的優化設計理論，在計算坐標下詳細推導了該優化設計理論，得到了計算坐標系下描述的共扼方程數學描述形式，並以給定目標壓力分佈的氣動反設計為例，導出了相應的共扼方程邊界條件，以及關鍵的梯度求解具體表達形式，為了求解方便，把計算空間上描述共扼方程表達形式變換到物理空間中進行描述，通過與ns方程表達形式對比分析，最終給出了一種直觀的共轆方程表達方式。
  6. An equation to calculate ultimate shear - resistant capacity of src column and steel beam joint is discussed, with consideration of the actions of concrete, steel web and horizontal hoop. the effects of axial press and steel wing under loads are also discussed

    探討考慮混凝土、型鋼腹板、箍筋共同貢獻的勁性柱?鋼梁節點極限抗剪承載力計算公式，並就軸壓力、翼緣在節點受力過程中的作用進行了分析與評價。
  7. We studied four eddy viscosity models ( evm ) and three nonlinear easm models in detail. the two - equation turbulence models are validated through simulating the flow fields over flat plate, airfoils and onera m6 wing. the capabilities of different turbulence models are accessed in this study

    加入兩方程湍流模型后，通過對平板、翼型、 oneram6機翼等繞流流場的數值計算，驗證了加入的各湍流模型的準確性，測試了它們對不同湍流流場的預測能力。
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