繞翼型的流動 的英文怎麼說

中文拼音 [ràoyìxíngdeliúdòng]
繞翼型的流動 英文
flow about airfoil
  • 繞 : 繞名詞1. [書面語] （彎曲） bend2. （姓氏） a surname
  • 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...
  • 的 : 4次方是 The fourth power of 2 is direction
  • 流 : Ⅰ動1 （液體移動; 流動） flow 2 （移動不定） drift; move; wander 3 （流傳; 傳播） spread 4 （向壞...
  • 流動 : 1. （液體或氣體移動） flow; run; circulate 2. （經常變換位置） going from place to place; on the move; mobile
  1. Numerical analysis of low - reynolds - number flow over airfoil

    繞翼型低雷諾數流動的數值分析研究
  2. This deforming method coupled with ale euler solver is applied to simulate unsteady transonic flow about oscillating airfoil ( 2 - d ) and oscillating rigid rectangular wing ( 3 - d ). computational results are in good agreement with experimental data

    本文將網格變形方法與數值解算器耦合起來求解了二維振動翼型繞流和三維振動矩形機翼繞流，計算結果與實驗結果一致，證明本文的數值方法具有較高的準確性。
  3. In order to set up the dynamic model of swimming micro robot, this dissertation builds up the statics model and analyses the micro motion amplifying performance of micro robot mechanism, builds up the vibration model of micro robot and analyses the vibrating performance without and with damp, researches the propelling force of driven wing and the resistance of micro robot in liquid based on the theory of flat board resisting stream, builds up the dynamic model of swimming micro robot for the first time in nation and analyses its swimming performance which is influenced by driving signal frequency, amplifying performance of main machanism, area of driven wing, character of fluid and so on. this dissertation manufactures the micro robot and sets up the experimental environment and tests the amplifying effect and the vibrating performance

    本文建立了主體機構靜力學模型，研究了主體機構的結構參數對微位移放大性能的影響；建立了主體機構振動模型，研究了主體機構在無液體阻尼和有液體阻尼情況下的振動特性；根據流體力學平板繞流理論，研究了驅動翼產生的推進力和微機器人在流體中受到的阻力；在此基礎上國內首次建立了泳動微機器人的動力學模型，並對模型進行了深入的研究，詳細闡明了驅動信號頻率、主體機構放大性能、主體機構振動特性、驅動翼面積、液體性質等因素對微機器人泳動特性的影響。
  4. 5. effects of unsteady flows on the aerodynamic characteristics are also analyzed. the results of this dissertation are useful for the further investigations of three - dimensional flapping wing

    對于非定常不可壓流動，分析了運動參數對翼型氣動特性的影響，為進一步研究繞三維撲翼的非定常流動打下基礎。
  5. In order to accelerate the convergence speed, we employ the local time step, and implicit residual smoothing methods. finally, we use this method to get the steady solution of the flow around naca0012 and naca4412 airfoil at very low speed and some basic unsteady solution

    本文對在低馬赫數下繞naca0012翼型和naca4412翼型的定常流場進行了求解，結果和實驗基本吻合，並對非定常運動情況進行了初步模擬研究，得出了一些有意義的結果。
  6. The numerical results of low - reynolds number flow around semi - infinite flat plate and airfoils are consistent with blasius solutions and references " data

    進行了低雷諾數下繞翼型流動的數值模擬，得到了正確的計算結果。
  7. The moving grid of type c - h for wing are generated by an algebraic procedure. the steady and unsteady transonic ( and subsonic ) viscous flows around wing are numerically simulated. the 3 - dimensional time - averaged compressible navier - stokes equations with b - l or j - k turbulent models are solved by the implicit lu - n7nd algorithm

    用代數方法生成機翼的c - h型運動網格，從三維非定常n - s方程組出發，利用lu - nnd有限差分格式和b - l或j - k湍流模型建立了一種數值模擬三維機翼的亞、跨、超音速定常及非定常粘性繞流的方法和程序。
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