wing configuration 中文意思是什麼

wing configuration 解釋
機翼構造
  • 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...
  • configuration : n. 1. 結構；構造；圓形，外形。2. 組合，布置；配置。3. 地形；【天文學】（行星等的）相對位置，方位；【化學】（分子中原子的）組態，排列；【物理學】位形；組態。
  1. Joined - wing configuration features diamond - shapes in both the plan and front views. the front wing is aft swept with positive - dihedral angle and the rear wing is forward swept with negative dihedral angle

    聯結翼飛機是指帶上反角的后掠前翼和帶下反角的前掠后翼聯結成菱形框架結構的飛機。
  2. In this paper, the major subject investigated is the ducted fan vertical take - off and landing ( vtol ) uav. compared with normal fixed - wing uav, it has so many strong points such as be convenient to take - off and land, good adaptability and long hover time. we analyze and summary information of foreign uavs, then calculate the figure dimension of our uav, and draw the uav structure configuration and the outside view drawing of three dimensional structure

    本課題的研究對象是涵道風扇式垂直起落無人機，與一般的固定翼無人機相比，它有著起落方便、適應性強、可以在空中長時間盤旋等優點，本文通過對相關飛行器資料的分析總結，給出了無人機的大體結構尺寸，並畫出了無人機的結構布局圖和三維結構外觀圖。
  3. Tailless flying wing aerodynamic configuration being optimal selection in ucav general layout design

    大展弦比復合材料機翼結構建模與氣動彈性分析
  4. Force measurement in a low speed wind tunnel was conducted to investigate the effects of the height of a distant canard wing on the longitudinal aerodynamic characteristics of a forward - swept configuration

    摘要基於前掠翼鴨式前翼布局的風洞測力實驗，分析了距離主機翼較遠的鴨翼相對于主機翼的高度對布局縱向氣動性能的影響。
  5. 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。
  6. 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。
  7. Compared with a delta wing aircraft, the double - delta wing configuration has better aerodynamic performance at high angles of attack. an operational analysis was introduced as a method for evaluating training effectiveness of trainer aircraft. approaches to the engineering estimation of aerodynamic characteristics for aircraft with a double - delta wing configuration were studied, and the procedures for determining aircraft performance indices formulated. taking training effectiveness as the objective function and geometric parameters of the wing platform as design variables, through a numerical multivariate optimization arithmetic, the conceptual design optimization for a certain fighter trainer aircraft with double - delta wing configuration was carried out under the constraints of tactical and technical requirements and interrelated geometry. agreement of a calculation example with engineering practice indicates that the optimal design has higher training effectiveness than the baseline design, and in addition, improves the structural force - bearing conditions

    雙三角翼氣動布局比三角翼飛機具有更好的大攻角空氣動力特性.引入了評估教練機訓練效能的作戰分析法，研究了雙三角機翼布局飛機空氣動力特性的工程計算途徑以及飛機性能指標的確定方法.以訓練效能作為目標函數並選取機翼平面形狀的幾何參數為設計變量，採用多變量數值尋優方法，在戰術技術指標及相關幾何約束條件下，對某高級教練機的雙三角機翼氣動布局方案進行了優化選擇.算例表明最優方案不僅比原準方案具有更高的訓練效能，還改善了結構的受力情況，與工程實踐吻合
  8. Taking m6 wing and f4 wing - body configuration as computational examples, some results by solving euler and n - s equations are presented. compared with the results of wind tunnel experiment, the results of n - s solver are much better than those of euler solver, and the upwind scheme is better than the central scheme in catching shock wave

    本文以m6機翼和f4翼身組合體為算例，對euler方程和n - s方程的計算結果進行了比較，從算例上可以看出， n - s方程的計算結果更接近實驗值；對中心差分格式和迎風格式的比較，可以看出，在激波的捕捉方面，迎風格式比中心差分格式更精確。
  9. The aerodynamics investigation of the joined - wing configuration

    連接翼布局氣動特性研究
  10. This configuration will allow him to reach the solar wing and investigate the problem

    這種結構形態可以使他到達太陽能翼以了解問題所在。
  11. It is possible to change tyres, fill the fuel - tank, and modify the wing configuration

    這是有可能改變輪胎，填補油箱問題，並修改聯隊配置。
  12. The viscous flow around m6 wing and f4 wing - body configuration are simulated and compared with the results of wind tunnel experiment

    為了驗證方法和程序的正確性，論文中對m6機翼和f4翼身組合體的流場進行了數值模擬，並與試驗結果進行了對比。
  13. The elegant ship featured an articulated wing system that deployed the wings in a splayed, lateral configuration during flight

    這優雅的船有特別的鉸鏈機翼系統，在飛行期間把機翼展開為舒展的側面結構。
  14. Solution - based grid adaptations are carried out, and efficiently capturing flow features. 5. coupled with the cartesian grids, a store separation for wing / store configuration is studied

    6 .對於二維多段翼型繞流，利用混合網格完成了navier一stokes方程的數值模擬。
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