翼身合體 的英文怎麼說

中文拼音 [yìshēngětǐ]
翼身合體 英文
wingbody
  • 翼 : Ⅰ名詞1 （翅膀） the wing of a bird 2 （像翅膀的東西） the wing of an aeroplane etc : 鼻翼 wing of...
  • 身 : Ⅰ名詞1 （身體） body 2 （生命） life 3 （自己; 本身） oneself; personally 4 （人的品格和修養） on...
  • 合 : 合量詞（容量單位） ge, a unit of dry measure for grain （=1 decilitre）
  • 體 : 體構詞成分。
  1. 3. taking use of wing - fuselage fusion lifting body design technology, which not only achieves good aerodynamic characteristic, but also is good to stealth and agility to system arrange. 4

    採用翼身全融合?升力體設計技術，不僅獲得了優越的氣動性能，而且也將對隱身性能帶來好處，為總體布置和裝載帶來極大的靈活性。
  2. 2. the transonic flow field solutions of a ttcp standard waf - body combinations are computed using the software of cfd, the results are agreement with experiment dates, this verifies that the accuracy of the numerical simulation model is ensured

    2 .應用cfd軟體對某ttcp標準卷弧翼-身組合體跨聲速下流場進行數值計算，將計算結果與文獻試驗結果進行對比，驗證本文數值計算模型。
  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. Until recently, however, their use has been confined to projects such as refining the aerodynamic profiles of car bodies, aircraft fuselages and wings

    直至最近之前，它們還一直被局限於例如改進汽車車體、飛機機身和機翼的符合空氣動力學的外形上。
  6. 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。
  7. 3 ) generating the 3 - d unstructured grids for the combination of wing - body by means of afm ( advancing front method ). using a new criterion for selecting the optimum point. the method is proved to be feasible

    （ 3 ）由生成的三維初始推進面，應用推進陣面法完成了翼身組合體的三維空間網格生成並嘗試了一種新的推進選點準則，實踐證明是可行的。
  8. 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。
  9. The numerical examples show that the current multigrid method is efficient and robust for solving of both 2d and 3d flow equations in inviscid and viscous flows. the parallel - computation example also indicated a high parallel computing efficiency was achieved

    選用了兩種翼型、 m6機翼、 m100的機翼、某三角翼和dlr - f4翼身組合體等多個算例對本文多重網格法進行了驗證。
  10. 4 ) the euler equation is solved for the combination of wingbody by means of the finite volume method on the unstructured grids. several methods are used for quick convergence and the results are in correspondence with the experiment data

    （ 4 ）應用格心格式的有限體積法對翼身組合體繞流進行了euler方程的數值模擬，同時引入各種加速收斂措施，與實驗相比，得到了較為滿意的計算結果。
  11. 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。
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