airfoil design 中文意思是什麼
airfoil design
解釋
翼形設計-
As design studies progressed it was found that several airfoil shapes could be used to satisfy the new performance criteria.
當進行設計的研究工作后，發現有幾種翼型可以用來滿足新的性能指標。 -
Three kinds of trapezoid, delta and airfoil shaped vortex generators are designed based on traditional, sub boundary layer and micro - vortex generators conceptual design, to study the influence of the shape, height, aspect ratio, chordwise position, spanwise position and direction angles of vortex generators on boundary layer separation control
（ 5 ）綜合分析研究了渦流發生器的工作原理和設計原則。根據國內外資料，研究了渦流發生器形狀、高度、展弦比、尖削比、弦向位置、展向位置和方位角等因素對附面層分離控制效果的影響。 -
Proceed from the angle of energy and taking considerations on interference factor and drag of airfoil profile, a kind of new typed calculation method on the design of vane air foil was put forward according to the vortex aerodynamics model of the rotor of wind turbines with horizontal axis
摘要根據水平軸風力機轉子的渦流氣動模型，從能量的角度入手，考慮干涉因子和翼型阻力，提出了葉片翼型設計的一種新型計算方法。 -
Abstract : the effects of airfoil geometric parameters on wing " s spacial and polarized scattering characteristics have been systematically revealed. the results of the study indicated that the calculating value of diffraction from trailing edge by using the formula of the straight wedge is very far from experimental results for vertical polarization, and the contribution of thickness of the trailing edge to scattering must be considered in the calculation. the scattering peak of leading edge depends only on radius of airfoil for horizontal polarization. but for vertical polarization, it depends on maximum thickness and the location of maximum thickness. engineering formulas for evaluating all scattering peaks were given in the paper. it is important for the design of low - rcs wing
文摘:系統地揭示了翼形幾何參數對機翼的空間散射特性、極化散射特性的影響規律.研究發現，在垂直極化狀態下用理論尖劈公式計算機翼后緣繞射的計算結果與實驗結果相差甚遠.提出在垂直極化狀態下機翼后緣繞射的計算必須將后緣厚度考慮在內的見解.對於水平極化，前緣散射波峰只與前緣半徑有關；而對於垂直極化，前緣散射波峰與翼形最大厚度以及最大厚度位置有關.給出前後緣散射波峰的工程估算公式，為低雷達散射截面（ rcs ）機翼設計提供依據 -
In the design page, submit the form to design the first airfoil
在設計頁，遞交表格設計第一翼型 -
The effective optimization design programs for different cases are developed by integrating the following several aspects which involves the flow analysis, adjoint equation solution, gradient solution, optimal arithmetic and grid generation. some practical design tests for airfoil and wing show that the continuous adjoint approach is very effective and useful method for aerodynamic optimization design. at the same time, we have done the research of aerodynamic optimum design for airfoils by using navier - stokes equations
（ 4 ）研究了基於控制理論和三維navier一stokes方程的優化設計理論，在計算坐標下詳細推導了該優化設計理論，得到了計算坐標系下描述的共扼方程數學描述形式，並以給定目標壓力分佈的氣動反設計為例，導出了相應的共扼方程邊界條件，以及關鍵的梯度求解具體表達形式，為了求解方便，把計算空間上描述共扼方程表達形式變換到物理空間中進行描述，通過與ns方程表達形式對比分析，最終給出了一種直觀的共轆方程表達方式。 -
Abstract : an effective aerodynamic optimization design method of transonic airfoil is given
文摘:提出了一種有效的跨音速翼型氣動優化設計方法。 -
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。 -
The dissertation presents the combined theoretical, numerical and experimental studies on the experimental modeling of the actuator, the design of test rig and control system, the modeling of two - dimensional airfoil aeroelastic system, the control design of active flutter suppression, and the effect of group delay in the digital filter on the stability of aeroelastic closed - loop system
本文通過理論分析、數值模擬與風洞實驗相結合的方法，研究了超聲電機作動器建模、翼段顫振實驗裝置和控制系統設計、二維翼段氣動彈性系統建模、顫振抑制控制律設計以及數字濾波器群時延對顫振抑制閉環系統穩定性影響等問題。 -
In this thesis, a system planning of assembly sequence planning module in virtual assembly system is proposed which is based on analyzing the characteristic of airfoil assembly and assembly design. the core techniques of assembly sequence planning which based on genetic algorithm and fuzzy set theory are investigated in detail. main research work and achievements are as follows : 1
本文在分析飛機機翼裝配特點的基礎上，完成了虛擬裝配系統中裝配順序規劃模塊的設計與實現，並對基於遺傳演算法及模糊集理論的裝配序列規劃技術進行了深入研究，主要研究內容包括： 1 -
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。 -
In this paper, the boundary layer characteristics of a supercritical airfoil is researched in wind tunnel. from the start to control boundary layer separation and to improve aerodynamics characteristics of this airfoil, three kinds of trapezoid, delta and airfoil shaped vortex generators are designed based on traditional, sub boundary layer and micro - vortex generators conceptual design. it include as follows : 1
研究工作中，從控制該翼型附面層分離、提高大迎角氣動性能的角度出發，通過風洞實驗研究，研究了該翼型的附面層特性和氣動性能，針對其附面層特性，給出了梯形、三角形和翼型式三種渦流發生器設計方案，為下一步研究工作奠定了堅實基礎。 -
The target of this thesis is to develop a design and optimization tool for airfoils of wind - in - ground air vehicle. the functions of the tool include : to generate wing - in - ground air vehicle airfoil by relative less control points, to simulate the wing - in - ground effect by the mirror method, to analyze aerodynamic performance of the airfoil using the software javafoil and to optimization the airfoil by the based - surrogate optimization method
該軟體具有如下特點:給出較少的控制點生成一個地效飛行器翼型;採用鏡像法來模擬地面效應，應用可以計算地面效應的翼型分析軟體javafoil對地效飛行器翼型的空氣特性進行分析;應用基於代理模型的優化方法對地效飛行器翼型進行優化。 -
The joukowski airfoil problem is the simplest application of conformal mapping to airfoil design
Joukowski問題是最簡單的翼型形映射應用到機翼設計 -
Solving method for inverse problem of unsteady aerodynamic design of 2 - d oscillating airfoil based on euler equations
二維機翼非定常氣動反命題的歐拉解法 -
Provide the experimental research scheme to measure and diagnose boundary layer of airfoil. the satisfied results demonstrated that this scheme is correct and efficient. it provides the reliable foundation on analysis of boundary layer characteristics and vortex generators " design
研究結果表明，該方案是正確的，既切實可行、節約了實驗經費，又獲得了滿意的實驗結果，為分析附面層特性和渦流發生器的設計提高了可靠依據。 -
Modal controller design of defective system and its application in flutter control of an airfoil
虧損系統模態控制設計及其在機翼顫振控制中的應用 -
On improving multi - objective optimization of airfoil design with complex optimum method
基於復合形方法的翼型優化設計研究 -
To put the method in some perspective, it helpful to briefly outline the two general approaches to airfoil design
把一些觀點方法，它有助於扼要介紹兩個一般方式翼型設計 -
In this paper based on the optimization design method using control theory for airfoils, a design method for multi - element airfoils is developed with the chimera grids. and optimization computation for reducing drag of shockwave of single airfoil in transonic flow is also successful
本文的主要工作是：以在控制理論進行單段翼型優化設計的基礎上，利用嵌套網格技術將其發展為適用於帶襟翼多段翼型的優化設計。
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