尾翼升力 的英文怎麼說

中文拼音 [wěiyìshēnglì]
尾翼升力 英文
tail lift
  • 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...
  • 升 : Ⅰ動詞1 （由低往高移動） rise; hoist; go up; ascend 2 （等級提高） promote Ⅱ量詞1 （容量單位） lit...
  • 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...
  • 尾翼 : [航空] tail surface; empennage; tail; tail assembly; tail fin; tailpiece
  1. Flying boat is a controllable aircraft that can flying in the air, the flotage provided by the helum - filled bag inside the flying boat can support the boat and it s load in the air, motor pushing it forward ; the direction is guided by the device on it s tail, going down of the boat is made by escaping the gas inside, it can rise or fall straightly or stay in the air, no necessity of special site for taking off

    飛艇是一種可操縱的浮於空中的飛行器。在飛行中主要依靠內部充滿氦氣的氣囊提供的浮力，將飛艇及其載荷支持在空中，發動機為其提供前進的動力，通過操縱尾翼上的升降舵和方向舵控制飛艇的俯仰和方向運動，飛艇的下降是通過排放氣來實現的。飛艇可以垂直起降空中懸停，不需要有專用設備的起降場。
  2. The results of the lift interference are given here as a result of a series of rudder of different aspect ration fitted to different location of the fornication. in the second part, the device of open water experiment of ichthyoid rudder is present

    提出了一個估算魚形舵定常升力的方法，計算了一系列不同展弦比、不同翼型、不同位置分叉點及尾緣剖分角對魚形舵影響下的升力。
  3. The aerodynamic characteristics of a projectile with wrap around fins are studied systematically in this paper, as follows : 1. the lift coefficients 、 drag force coefficients 、 pitch moment coefficients 、 pitch damping moment derivatives and roll damping moment derivatives are obtained from engineering calculation through looking wrap around fins as flat fins of the same projection aera

    本文對某卷弧尾翼彈氣動特性進行了系統研究，主要內容與結論為: 1 .將卷弧翼按照相同投影面積的平板翼進行工程估算，得到升力系數、阻力系數、俯仰力矩系數、俯仰阻尼導數、滾轉阻尼導數曲線。
  4. Based on the green ' s formula and the assumption of the propeller blade ' s thin sections, a lifting - surface method of propellers with the vortex lattice and equal source panel distributions on the mean camber surface has been introduced for the prediction of steady propeller ' s hydrodynamics in this paper. an approximate kurta condition was applied

    基於creen公式和薄翼理論假設導出的升力面方法，採用在螺旋槳拱弧面上分佈離散渦、源布置方法預報均勻流場中的螺旋槳的定常性能，螺旋槳尾渦面上壓力連續性條件採用近似的kutta條件處理。
  5. The design of configuration and other primary structures of the helicopter have been finished. in order to analysis the stability and control of the helicopter, a flight mechanical modeling has been founded based on a single - rotor helicopter

    本文以常規單旋翼帶尾槳的直升機配平和操穩計算方法為基礎，建立了帶涵道共軸式直升機飛行動力學模型，對碟形無人直升機進行了配平和操縱性和穩定性分析計算。
  6. 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。
  7. 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。
  8. The tail lift curve slope as determined from the panel model may require adjustment in order to apply the test results.

    為了應用試驗結果，根據翼段模型試驗確定的平尾升力曲線斜率可能要作些修正。
  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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