trailing edge surface 中文意思是什麼
trailing edge surface
解釋
后緣操縱面-
Abstract : a model of self - excited ae rodynamic forces acting on a sectionof bridge deck with additional surface atta ched below the trailing edge is established
文摘:首先建立了下風側附加翼板橋梁主梁截面的自激氣動力模型。 -
Trailing edge of fork crown and frame down tube present a virtual continuous surface to the wind. reducing aerodynamic drag
前叉肩部的延伸邊緣和車架的下管形成一個虛擬的連續迎風面，從而有效地減少風阻。 -
A variable control surface on the trailing edge of an aircraft wing, used primarily to increase lift or drag
襟翼飛機后翼上最初用來增加上升力或拖力的可靈活控制的輔助翼 -
The primary purpose of this paper is how to solve the overloaded propeller ' s condition. the style of propeller trailing edge cutting and shave on the pressure surface is adopted. the propeller ' s actual effect pitch will be reduced which cause the propeller ' s torque down
本文主要是考慮螺旋槳出現負荷過重時如何處理的問題，所以採用槳葉隨邊切割並在葉面處將翼型修順的方式，實質上是切割后導致螺旋槳實效螺距的減小，從而使螺旋槳吸收的轉矩降低來達到主機負荷降低的目的。 -
The surface panel method has been applied to predict the hydrodynamic performance of highly skewed propeller. the surface of propeller and its trailing vortex are discreted by a number of small hyperboloidal quadrilateral panels with constant source and doublet distribution. for highly skewed propeller, the conventional method generating grid oriented along constant radii will result in a high aspect ratio and a high skewness and a twist panel near the propeller tip on blade surface, which result easily in incorrect calculation results of velovity on blade surface, even in iteration divergence and calculation failure. a “ non - conventional grid ” is developed to acoid these problems. this grid can effectively solve the problem of the calculation and convergence for highly skewed propeller. the non - linear kutta condition of equal pressure on upper and lower at the trailing edge is executed by the iterative procedure. by sample calculating, the obtained results are satisfied the experimental data
採用面元法預報大側斜螺旋槳水動力性能，螺旋槳表面及尾渦面離散為四邊形雙曲面元，每個面元上布置等強度源匯和偶極子分佈.對于大側斜螺旋槳而言，槳葉表面採用常規的等半徑網格劃分方法在近葉梢處將導致大展弦比、大側斜和扭曲面元，這容易使槳葉表面速度的計算結果不正確，甚至會導致迭代過程發散及計算失敗.文中建立了一種「非常規網格」劃分方法，能有效地解決大側斜螺旋槳的計算和收斂問題.槳葉隨邊處通過迭代實現非線性等壓庫塔條件 -
The computer program has following advantage : the solution of main blade is by iterative scheme in time domain, the kutta condition is used by explicit equal pressure condition, the jacobian matrix which can reflect the influence on the difference between the upper and lower surface at trailing edge by dipole is calculated in each iterative procedure, in order to improve the convergence of iteration
本文編制的螺旋槳非定常性能預報程序是針對主葉在時域中迭代求解的， kutta條件採用的是顯式的等壓條件，求解中為了提高迭代的收斂性，在每次迭代中都重新計算反映偶極子強度對尾緣處上下表面壓力差影響的jacobi矩陣。 -
In lifting - surface theory, the non - liner phenomena of the trailing vortex in the transition wake area and of the tip vortex separation are considered. in surface panel method hyperboloidal quadrilateral panels are employed and the morino ' s analytical formulation is used to determine the influence coefficients. the more reasonable pressure kutta condition is satisfied at the trailing edge of propeller blade
在計算中，對于升力面理論，本論文考慮了過渡區尾渦收縮和葉梢分離的非線型現象的影響；對于面元法，本論文採用的是計算較為簡便的基於擾動速度勢的基本公式及雙曲面形狀的面元，在槳葉隨邊滿足更趨合理的壓力kutta條件，並用morino導出的解析公式計算面元的影響系數的快速有效的數值預報方法。 -
The analysis shows that the additional surface attached below the trailing edge is an effective aerodynamic means for suppressing the flutter of suspension bridges
分析表明，主梁下風側附加翼板對懸索橋顫振是一種有效的氣動控制措施。 -
On the rotor blade pressure surface, the dominant frequencies of unsteady surface pressure are the up - stream blade wake passing frequency and its harmonics, and the amplitudes of pressure fluctuations decrease from leading edge to trailing edge
轉子葉片吸力面非定常壓力受葉片附面層和上游葉片尾跡共同影響，其主導頻率為上游葉片尾跡頻率及其倍頻，但是在吸力面前部氣流加速區壓力波動幅度沿流向增大，而在吸力面後部氣流減速區壓力波動幅度沿流向減小。
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