wing lift 中文意思是什麼

wing lift 解釋
機翼升力
  • 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...
  • lift : vt 1 舉起，使升起，提起，抬起；提高；提升。2 使高尚；鼓舞。3 運送，搬運；空運 （ ＝ airlift） 4 ...
  1. The method of wing shape optimization of space shutlle has been developed with penalty function approach in which the objective function is the mass of the wing and the constraints are the hypersonic re - entry flight cross range, lift / drag ratio, and subsonic flight lift / drag ratio, the margin of the longitudial static stability and the magnitude of the horizontal landing speed etc

    摘要介紹了在滿足高超音速再入橫向機動航程，高超音速再入飛行時的升阻比，亞音速進場飛行時的升阻比，縱向靜穩定性裕度和水平著陸速度等飛行性能設計要求下，用罰函數法尋求使航天飛機機翼質量為最小的外形優化方法並給出了算例。
  2. The effects of body - strake on lift characteristics of the double - delta - wing aircraft

    機身邊條對雙三角翼飛機升力特性的影響
  3. Much more increase of maximum lift - to - drag ratio can be obtained with a forward - swept main wing with a small sweepback angle leading edge

    主機翼前掠角較小時，鴨翼改善和提高陞阻比的效果比較明顯。
  4. In time, wilbur conceived an elegant cable - and - pulley mechanism that twisted a flexible fabric wing across its span so that one wingtip could generate greater lift and the other less

    最後，魏爾柏設計出精巧的纜索及滑輪機構，用以扭轉可彎折的布料機翼，讓兩邊翼尖產生大小不等的升力。
  5. As guffey notes, “ a long, slender wing, by its nature, would be lightweight and would provide very good lift and drag characteristics

    高非指出：窄長的機翼本來就比較輕，升力和阻力的特性也相當優異。
  6. An upper canard, which is in the vicinity height of forward - swept main wing, could improve the maximum lift - to - drag ratio

    高於主機翼的鴨翼對最大升阻比的改善較多，但也不宜過高。
  7. Tenders must be placed in the government secretariat tender box situated in the lift lobby on the lower ground floor of the central government offices east wing before 12 noon on friday, january 21, 2000. end friday, december 10, 1999

    投標者必須於二零零零年一月二十一日星期五中午十二時前，把投標書放入中區政府合署東座地下低層電梯門廊的政府總部投標箱內。
  8. Tenders must be placed in the government secretariat tender box situated in the lift lobby on the lower ground floor of the central government offices ( east wing ) before 12 noon on friday, january 21, 2000. endfriday, december 10, 1999

    投標者必須於二零零零年一月二十一日星期五中午十二時前，把投標書放入中區政府合署東座地下低層電梯門廊的政府總部投標箱內。
  9. Tender proposals should be placed in the government secretariat tender box at the lift lobby of the lower ground floor of the central government offices ( east wing ), 20 lower albert road ( at its junction with garden road ), hong kong, before noon on june 17, 2005

    投標者必須於二五年六月十七日中午十二時前，把投標書放入香港下亞厘畢道二十號（近花園道口）中區政府合署東座地下低層電梯門廊的政府總部投標箱內。
  10. Tender proposals should be placed in the government secretariat tender box at the lift lobby of the lower ground floor of the central government offices ( east wing ), 20 lower albert road ( at its junction with garden road ), hong kong before 12 noon on april 22, 2005

    投標者必須於二五年四月二十二日中午十二時前，把投標書放入香港下亞厘畢道二十號（近花園道口）中區政府合署東座地下低層電梯門廊的政府總部投標箱內。
  11. 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。
  12. A part or surface, such as a wing, propeller blade, or rudder, whose shape and orientation control stability, direction, lift, thrust, or propulsion

    翼剖面；機翼；翼面一個部件或平面，如機翼、螺旋槳葉、方向舵等，其形狀或方位控制穩定性、方向、抬升、沖擊或驅動
  13. This induced flow produces a positive moment that increases with wing lift or a.

    這一誘導氣流產生正的力矩，該力矩隨升力或迎角a的增加而增加。
  14. A variable control surface on the trailing edge of an aircraft wing, used primarily to increase lift or drag

    襟翼飛機后翼上最初用來增加上升力或拖力的可靈活控制的輔助翼
  15. Canard wing increases lift coefficient with the penalty of the increase of drag coefficient

    低於主機翼的鴨翼將加強前掠翼布局的緩失速特性。
  16. Multi - gap - fowler - flap, while deflecting its rudders, simultaneously extends backwards by relatively large scope, which broaden the overall wing - camber and area, so that more additional lift could be attained through improving air - flow boundary layer

    多縫富勒襟翼在襟翼舵面偏轉的同時發生較大幅度的後退，增加機翼整體彎度和機翼面積，通過縫隙氣流改善附面層狀況，因而得到加大的升力增量。
  17. Based on the mechanism of slipstream interaction, described in this thesis is firstly the interaction of the propeller slipstream with the wing 、 fuselage and horizontal tail. subsequently, the changes in lift 、 drag and pitching moment are derived, giving an engineering model for the prediction of the increments in the aerodynamic characteristics caused by the interference between the propeller slipstream and the other parts of aircraft. this method offers a powerful means to the calculation of the aerodynamic interaction between the propeller and the aircraft, providing reliable data for the design of and aerodynamic calculation on propeller - powered aircraft

    本文以滑流干擾的機理為出發點，研究了螺旋槳滑流與飛機機翼、機身、平尾組合體之間的相互影響，推導出滑流引起的飛機升力、阻力和俯仰力矩的變化，給出了滑流干擾對機體氣動特性影響的工程估算方法，為研究螺旋槳與飛機部件之間的相互干擾提供了有力的工具，為以螺旋槳發動機為動力的飛機的設計和氣動計算提供可靠的依據。
  18. Lastly, previous vane are analysed by fluent, we calculate the pressure distribution chart and report chart of each wing form, then alter the torsion angle and the airfoil form of the vane respectively, finally ascertain the influence curve of the torsion angle and the airfoil form of the vane on which act the lift power

    最後，通過fluent對設計出的葉片分析，得出其壓力分布圖和報告圖。然後從改變葉片的扭轉角度和翼型兩個方面分析其對升力和阻力的影響。得出葉片的扭轉角和翼型對升阻比的影響曲線，在文章的結尾部分估算了無人機的一些性能參數。
  19. It is concluded that all of the tested bionic wings can generate lift force, however the flexible wing has best kinetic and aerodynamic performance among them, as well as flapping frequency and amplitude are the main factor of effecting on lift force generation

    實驗結果表明，研製的翅型都能產生一定的升力，其中柔性翅具有較好的運動性能和氣動性能，並且拍動頻率和拍動幅度對升力有較大影響。
  20. In this thesis, finite volume method and dual - time stepping method are employed to solve the 3 - d unsteady euler equations. the unsteady flow field around a finite - span flapping wing is simulated. the lift and thrust of the flapping wing for different cases are calculated

    本文運用有限體積法結合雙時間推進技術求解三維非定常歐拉方程，模擬了有限翼展機翼在同時具有上下拍動和俯仰運動狀態下的非定常流場，計算了不同狀態下撲翼的升力及推力，分析了各個影響因素對撲翼氣動特性的影響。
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