尾流阻力 的英文怎麼說

中文拼音 [wěiliúzǔlì]
尾流阻力 英文
drag; wake
  • 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...
  • 阻 : 動詞（阻擋; 阻礙） block; hinder; impede; obstruct
  • 力 : Ⅰ名1 （力量; 能力） power; strength; ability; capacity 2 [物理學] （改變物體運動狀態的作用） forc...
  • 阻力 : 1 （阻礙事物發展的外力） obstruction; resistance 2 [物理學] resistance; drag; drag force; nowel; ...
  1. The wake survey cannot be used to measure the drag of stalled airfoil or of airfoils with flaps down.

    尾流測量不能用來測量失連狀態下的冀型或襟翼偏轉后的翼型阻力。
  2. The software designed for the system is validated by experiments and proved correct. the system can s imulate the real air - stream and put it on missile ' s wings to make them work under the same force environment as the real spread process, so the relationship of explosive stuff and attack angle can be calculated

    本文所設計的監控軟體已通過實際系統的驗證，說明整個系統的設計是合理正確的，能夠真實的模擬力矩，產生一種類似真實氣流阻力的載荷，並將其正確施加於彈翼（尾翼）上，使彈翼（尾翼）能在與展開過程中實際受力相同的狀態下工作。
  3. The paper introduces experience of selecting hydraulic calculation formula and illustrates calculation of critical velocity of flow ( or critical pipe diameter ) and friction loss of pressure pipe in tailings transport and how to select the formula with examples

    介紹工程實踐中，選用水力計算公式的體會，對尾礦輸送中臨界流速（或臨界管徑）和壓力管道摩阻損失的計算以及如何選用公式分別作了舉例說明。
  4. Stay cable, which is one of the important components in cable - stayed bridges, is susceptible to environmental excitation because of its small weight, large flexible, low damping, then the various vibration is induced, such as vortex - induced vibration, wake galloping, rain vibration, buffeting as well as parametric - induced vibration etc. in this paper, the vibration property of stay cable has firstly been introduced

    斜拉索是斜拉橋的重要承力構件，由於拉索自身的質量輕、柔度大、阻尼小，在外界激勵下，易發生各種振動，包括渦激振、尾流馳振、風雨振、抖振以及參數振動等。
  5. 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。
  6. The load control system has already passed the test ' s validate. it shows that the design of whole system is correct. the system can truly simulate the real air - stream and put it on missile ' s wings to make them work on the same force situation as in the real spread process, so the relationship of explosive stuff and attack angle can be confirmed

    本文所設計的加載控制系統已通過實際系統的驗證，說明整個系統的設計是合理正確的，它能夠真實地模擬類似真實氣流阻力的載荷，並施加於彈翼或尾翼，模擬其在真實工作環境下的受力狀態，可以測算導彈攻角與火工品填藥量的關系。
  7. The results are compared with the cases in a single - layer fluid, showing that the density stratification can have a relative large effect on the drag and lift coefficients as well as the vortex shedding

    計算受迫振蕩圓柱體的升力系數、阻力系數隨時間的演化曲線和圓柱體的尾渦分佈，以及圓柱體的受迫振蕩激發兩層流體內界面的擾動，並與均勻流體的情況進行了比較分析。
  8. The relationship between the non - dimensional drag coefficient of sma plate face and time is presented, and the pressure distribution on and around the sma plate surface as well as the karman vortex configuration in the wake at a certain time are given

    給出了形狀記憶合金薄板表面的流體無量綱阻力系數隨時間的變化關系，同時給出了某一時刻薄板表面及其周邊的壓力分佈和薄板尾跡中的卡門渦街形態。
  9. A kind of grid generation method based on two - dimension poisson equtions is devlop - ed into the grid generation method based on three - dimension poisson equtions in this dessertation. use this method, this paper generals the grids of glide bullet to increase range that is at three states, that is with no control rudder and no tail wing, only with tail wing and with control rudder and tail wing. this paper has calculated the aerodynamic coefficients of glide bullet to increase range that is at three states. beside this the paper has given the results and analysised the differences of the three states, and the effects of control rudder and tail wing to the lift and drag. this can give us some information about the ability of the control ruder and tail wing for increasing the range

    本文在二維泊松方程網格生成方法的基礎上推導出了一種三維泊松方程網格生成方法。並利用該方法生成了繞彈體、尾翼彈、滑翔增程彈三種不同彈形的流場網格。計算了超音速來流下彈體、尾翼彈，滑翔增程彈三種不同彈形的空氣動力學系數，分析了三種不同彈形計算結果的差別；分析了控制舵和尾翼對升力和阻力的影響。
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