model airfoil 中文意思是什麼
model airfoil
解釋
模型機翼-
Proceed from the angle of energy and taking considerations on interference factor and drag of airfoil profile, a kind of new typed calculation method on the design of vane air foil was put forward according to the vortex aerodynamics model of the rotor of wind turbines with horizontal axis
摘要根據水平軸風力機轉子的渦流氣動模型，從能量的角度入手，考慮干涉因子和翼型阻力，提出了葉片翼型設計的一種新型計算方法。 -
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。 -
Using method of oil - flow visualization techniques and measuring pressure distribution along airfoil chordwise and spanwise studies have been down for sidewall boundary - layer displacement effect in two - dimensional wind tunnel. three different chord models were tested in two different wind tunnel. in order to clarify the sidewall effects and study method of sidewall suction theory and sidewall interference correction method to remove effects of sidewall on model. the results of oil - flow test show that selection rational suction wary can obtain better testing results. by investigations on effects of the sidewall boundary layer suction and application of a sidewall interference correction method
為了很好地解決多機場航班隊列的擁塞問題，在將進場容量、離場容量與機場容量作為統一整體的情況下，充分考慮了機場間的網路效應，詳細研究了多機場航班隊列的優化問題，建立了多機場開放式非實時流量管理的數學模型，通過選取適當的決策變量，使其為線性0 - 1整數規劃模型，實現了中心流量集中管理.與其它演算法不同，本文提出的啟發式隱枚舉演算法能很好地解決此類問題，對某機場網路系統的模擬結果證明了所建模型、優化演算法及相應軟體的有效性和可靠性 -
Firstly, the paper analyzes the basic airfoil profile in theory. its forepart adopts ellipse column shape and its back - end adopts plane shape. simultaneously, the 3d parametrizing model is set up
首先，本文是從理論上對基準翼型進行了分析，前段曲線部分採用橢圓柱結構，后緣部分採用平面結構，建立了飛機機翼的三維參數化模型。 -
2. an unsteady, nonlinear state - space airfoil aerodynamics model was developed with onera dynamic stall model
對於後行槳葉的動態失速行為，引入了對翼型實驗數據不敏感，並也具有狀態空間形式的onera動態失速模型。 -
Then the steady and unsteady subsonic, transonic and supersonic viscous flows around airfoil and some aircraft are numerically simulated. the 3 - dimensional unsteady navier - stokes equations are solved using the implicit lu - nnd algorithm, with baldwin - lomax turbulent model. on the basis of simulating unsteady viscous flow, coupling the structure dynamics equations, the problems of static aeroelasticity and flutter are investigated for wings and elevator
在模擬非定常粘性繞流的基礎上，與顫振運動方程相耦合，分別對機翼和全機流固耦合現象中顫振問題進行了研究，準確求解跨音速顫振臨界速度，分析機翼和全機的從亞音速到超音速范圍的顫振規律，並研究分析了機翼飛行迎角變化對顫振速度的影響。 -
To get the good visual effect, the curve of airfoil is not rendered by simple lines and points, but lots of minuteness plane. what ' more, the airfoil model is depth - cued on screen
在繪制芯模時，為了實現良好的視角效果，在程序設計過程中，芯模曲面不是用簡單的線和點來描述，而是用許許多多的微小平面來描述的，並且使芯模在顯示屏幕上達到消隱的效果。 -
The test rig includes the airfoil model, the accompanied sensors, the actuator and the protecting mechanism
實驗裝置包含翼段模型、相關的傳感器及作動器、翼段安裝機構和保護裝置。 -
The main contributions of the dissertation are as follows. in chapter 2, the dissertation demonstrates the design of an airfoil model with a control surface driven by an ultrasonic motor as the actuator first, and then presents the experimental modeling of the actuator
論文的主要工作與學術貢獻如下: （ 1 ）設計了以超聲電機為作動器驅動控制面的二維翼段模型，並建立了作動器的傳遞函數模型。 -
In chapter 4, the aeroelastic model of the whole test rig is first established by using jones ’ s approximation of theodorsen ’ s unsteady aerodynamics load. then, the numerical simulations and wind tunnel experiments for the sub - optimal flutter suppression of the airfoil model are presented
數值模擬和風洞實驗研究表明，以超聲電機為控制面作動器可以有效地抑制翼段模型的顫振，顫振臨界速度提高了13 . 4 % ，數值模擬和風洞實驗結果基本吻合。 -
Secondly, agreement between the result from the mentioned eigenvalue arithmetic and the result from numerical calculation in the airfoil differential equation with runge - kutta method which obtain the trend of physical variable quantity demonstrate the fact that the assumed model and the given equations are valid
其次，通過用龍格?庫塔的數值方法對微分方程進行迭代，所求出的系統各振動量變化規律和上述算例的特徵值對比，結果是一致的。這就驗證了建模的合理性和方程推導的正確性。
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