airfoil surface 中文意思是什麼
airfoil surface
解釋
翼面-
This dissertation presents how to use the ultrasonic motor as an actuator to suppress the flutter of a two - dimensional airfoil section with a control surface. the ultrasonic motor, which features simple structure, high torque at low speed, small size, low weight and no electromagnetic contamination, is a promising actuator for the flutter suppression of small aircraft
超聲電機以其結構簡單緊湊、轉矩/質量比大、低速大扭矩、直接驅動，動態響應快、斷電自鎖和不產生磁場且不受外界磁場干擾等優點，有望成為一種非常有前途的作動器，用於小型飛機的機翼顫振主動抑制。 -
Time averaged temperature distributions on rotor surface will greatly change with the hot streak / airfoil ratio, and the temperature distribution changes more on the pressure surface than that on the suction surface of the rotor
改變熱斑數與導葉通道數比會對動葉時均溫度分佈產生較大影響，動葉壓力面溫度分佈所受的影響更大。 -
The main contributions of the dissertation are as follows. in chapter 2, the dissertation demonstrates the design of an airfoil model with a control surface driven by an ultrasonic motor as the actuator first, and then presents the experimental modeling of the actuator
論文的主要工作與學術貢獻如下: （ 1 ）設計了以超聲電機為作動器驅動控制面的二維翼段模型，並建立了作動器的傳遞函數模型。 -
We generated its grid surface on the fuselage or missile body according to the geometry projection relation between aerodynamic components and the bilinear interpolation approach. finally, we successfully developed a new algebra grid generation technique in virtue of the improved four - boundary interpolation. in this thesis, we put emphasis on the researches of aerodynamic inverse design and drag reduction questions for airfoil and wing using euler equations and control theory proposed by jameson
（ 2 ）進行了應用控制理論和二維歐拉方程的翼型氣動反設計，以及有升力約束情形下翼型跨音速減阻問題研究，分別推導了相應的共軛方程及邊界條件的數學形式，並給出了相應的梯度求解公式形式，研究發展了共軛方程及梯度的數值求解方法，成功進行了多個翼型的反設計和減阻問題研究。 -
3. the characteristics of boundary layer ' s transition, shape and separation are researched. the details as follows : ( l ) airfoil surface is turbulent boundary layer flows ; ( 2 ) velocity figure changed unsteady near the point of boundary layer separation due to randomicity of turbulent flow ; ( 3 ) the airfoil have better state of boundary layer separation and poor stall characteristics because of the upper surface of airfoil is flat
給出了該翼型的附面層特性：翼型表面基本為湍流附面層；在靠近附面層分離位置處，速度型形狀、特別是靠近翼型表面的底部速度型形狀變化不定，是湍流流動的隨機性所致；該翼型具有較好的附面層分離形態，但在失速迎角附近，附面層分離形態變化劇烈、失速特性差，是翼型上翼面形狀較為平坦所致。 -
Wu, c. j. & wang, l., 2003, adaptive optimal control of the incompressible flow around an airfoil with smart surface, proceedings of icfm4, dalian
王亮，吳錘結， 2003 ，用智能物面對非定常分離流進行最優自適應控制， 《空氣動力學新進展論文集》 ，北京 -
Upper surface of the airfoil
機翼上表面 -
In chapter five, algorithm of load identification is discussed in detail. levenberg ? marquardt algorithm and generalized regression neural network are used to identify the position and degree of the one load on the surface of the airfoil, correlation analysis algorithm of multi - load identification is also proposed in the paper
第五章重點論述了系統設計中的載荷識別演算法，採用人工神經網路lm - bp演算法及廣義回歸網路對單個載荷大小、位置進行了判定，提出了基於相關分析的多載荷識別演算法。
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