翼型繞流 的英文怎麼說

中文拼音 [yìxíngràoliú]
翼型繞流 英文
flow past airfoil
  • 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...
  • 繞 : 繞名詞1. [書面語] （彎曲） bend2. （姓氏） a surname
  • 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...
  1. Simulation of flow around an airfoil by the lattice boltzmann method

    方法的翼型繞流數值模擬
  2. 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
  3. On the base of the numerical simulation of unsteady viscous flows, the characters of the static aeroelastics and flutter for the wings are researched. some examples, simulating the steady and unsteady transonic ( and subsonic ) viscous flows around onera m6 wing, are given in this paper

    以oneram6機翼為算例，分別對其亞、跨音速定常及非定常粘性繞流狀態進行了數值模擬，並運用b - l和j - k兩種湍流模型計算結果和實驗數據進行了對比。
  4. 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。
  5. 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。
  6. Only clouds of points instead of grids are distributed over the computational domain and the spatial derivatives are estimated using a least - square curve fit on local clouds of points. the paper gives discrete form for euler equations on base of gridless method, and adopts five steps runge - kutta scheme for time - marching. the numerical results have been obtained for the 2 - d flows over airfoils or multi - element airfoils using the method presented

    本文首先對無粘euler方程進行無網格離散，並運用顯式runge - kutta格式推進求解，成功地數值模擬了二維單段和多段翼型的繞流；在此成功的基礎上通過在euler方程的右端加入粘性項，使求解方程變為層流navier ? stokes方程，得到了翼型繞流，數值結果顯示出粘性的影響。
  7. Icing research on airfoil and multi - element airfoil based on flow field and aerodynamic performance

    結冰對翼型和多段翼型繞流及氣動特性影響研究
  8. The three basic steps are as follows : firstly, the flow field is computed. secondly, the droplet trajectory equation is solved in order to determinate the limiting droplet trajectories and local collection coefficient. thirdly, a new iced shape is defined according to ice accretion model

    其基本步驟一般分三步：計算物體的繞流流場；求解水滴軌跡方程以確定極限水滴軌跡和收集系數；根據冰增長模型來確定新的結冰翼型形狀。
  9. 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。
  10. 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。
  11. Numerical simulation of viscous flow for multi - element airfoil using multi - block grids

    多段翼型粘性繞流多塊網格數值模擬
  12. 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。
  13. We studied four eddy viscosity models ( evm ) and three nonlinear easm models in detail. the two - equation turbulence models are validated through simulating the flow fields over flat plate, airfoils and onera m6 wing. the capabilities of different turbulence models are accessed in this study

    加入兩方程湍流模型后，通過對平板、翼型、 oneram6機翼等繞流流場的數值計算，驗證了加入的各湍流模型的準確性，測試了它們對不同湍流流場的預測能力。
  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。
  15. Convergence is accelerated by means of local time stepping, implicit residual smoothing. the numerical results have been obtained for the flows over n ac ago 12 or rae2822 airfoils

    並且基於點雲離散結構，引入了當地時間步長、殘值光顧等加速收斂技術，數值模擬了對稱和非對稱翼型繞流，獲得較好的計算結果。
  16. 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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