aerodynamic coefficients 中文意思是什麼

aerodynamic coefficients 解釋
氣動系數
  • aerodynamic : adj. 空氣動力學的。 an aerodynamic missile 飛航式導彈，有翼導彈。n. -s 空氣動力學，氣體力學。
  • coefficients : 系數
  1. These effects appear to be negligible with respect to aerodynamic coefficients.

    就空氣動力系數這方面來說，這些影響似乎可以略去。
  2. 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。
  3. Of all the aerodynamic parameters required in stability and control analysis, the hinge-moment coefficients are most difficult to determine with precision.

    進行穩定性和操縱性分析所需要的全部空氣動力參數中，鉸鏈力矩系數最難準確地確定。
  4. Effect of attack angle messurement error on extracting aerodynamic coefficients

    攻角誤差對擬合氣動系數的影響
  5. The measurements of discharge coefficients and pressure coefficients along the models with aspect ratios of 0. 5, 1. 0 and 2. 0 were carried out under various aerodynamic and geometric parameters ( reynolds numbers : 20000, 40000, 60000, 80000 ; suction rates : 0. 3, 0. 45 and 0. 6 ; rib angles : 45, 60, 90, 120 ; rib height - to - width ratio h / e : 1. 0 and 2. 0 ; film hole location : middle of ribs. upstream of ribs and downstream of ribs ). based on the abundant experimental data and figures, rules of discharge coefficients and pressure coefficients in dependence of geometric and aerodynamic parameters were given out

    根據實驗課題的要求，在寬高比分別為1 . 0 、 2 . 0和0 . 5的內流冷卻通道里，在不同的氣動和幾何參數（雷諾數re分別為20000 、 40000 、 60000 、 80000 ，出流比sr為0 . 3 、 0 . 45和0 . 6 ，肋角分別為45 、 60 、 90 、 120 ，肋高h e分別為1 . 0和2 . 0 ，孔位分別為肋中間、肋下游和肋上游）的情況下，對流量系數和壓力系數以及流場進行了實驗研究，獲得了大量的實驗數據和圖形，較為詳細地給出了流量系數和壓力系數隨不同氣動參數和幾何參數而變化的規律。
  6. Then the study algorithm is improved to enhance the identification result of the aerodynamic derivatives, and different bp anns are built to identify the static coefficients

    然後改進了學習演算法以識別橋梁模型的氣動導數，並採用了不同的bp網路識別橋梁模型的靜力三分力系數。
  7. Moreover, in order to capture the linear properties in aerodynamic coefficients, additional linear terms are added to the model, which make the wavelet network model has some definite physical significance in use

    另外，本文在小波網路模型中加入狀態變量的線性項，以反映氣動力系數中的線性特性，這對于實際應用是非常有意義的。
  8. Static coefficients are defined to describe the static effect of wind on bridge, and the aerodynamic derivatives are used to describe the aerodynamic effect

    靜力三分力系數用於描述風對橋梁的靜力作用，氣動導數是顫振和抖振分析方法的核心。
  9. Aerodynamic coefficient identification is a interdisciplinary subject between mechanics, informatics and control theory. this thesis also gives an overview of the development direction in this field, especially introducing the application of neural network in the aerodynamic coefficients identification, which gives the theoretical basis of using wavelet network in modeling of aerodynamic coefficients

    氣動系數辨識為介於力學、信息學和控制論之間的一門交叉學科，本文對該領域的發展方向進行了分析，其中特別分析了神經網路在氣動力系數建模中的應用狀況，這為本文採用小波網路氣動系數建模打下理論基礎。
  10. In the paper, the computational results of all models are obtained, including 3 - d velocity field, 3 - d pressure field, and six aerodynamic coefficients. the results have good agreement with wind tunnel test

    文中得出了客車外圍流場的速度矢量圖和壓力分布圖以及六個氣動力系數，並將最終結果與風洞試驗結果進行了比較，結果吻合較好。
  11. 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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