翼型力 的英文怎麼說
中文拼音 [yìxínglì]
翼型力
英文
profile force-
F72785 - 572 elevator rudder aileron power control unit test equipment
F72785 - 572型升降舵方向舵副翼動力控制裝置測試儀The wake survey cannot be used to measure the drag of stalled airfoil or of airfoils with flaps down.
尾流測量不能用來測量失連狀態下的冀型或襟翼偏轉后的翼型阻力。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。The effect of reynolds number on rudder hydrodynamic performance is also analyzed. up to the stall angle the computed lift and drag agree well with measurements and other author ' s calculations, whereas stall angle, lift and drag beyond the stall angle are slightly under - predicted. the solver is used to investigate laminar and turbulent separated flows around a 6 : 1 prolate spheroid at high incidence angles and their effects on hydrodynamic forces
應用所開發的求解器，以naca0015翼型舵為算例計算了船舵在不同雷諾武漢理三;大學博士學位論文數下大舵角范圍內的三維粘性流場及水動力，成功地預報了舵的失速角和最大升力，並初步探討了雷諾數對舵水動力的影響;計算結果與現有試驗和計算數據比較，吻合程度相當好，初步檢驗和驗證了該求解器精確模擬粘性流動和計算水動力的能力。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。Firstly, the airfoil ' s classic flutter ( at small attack angle ), stall flutter ( near the static stall angle ) and response ( at large attack angle ) are analyzed. it is found from the numerical results that " lock - in " will occur at certain freestream velocity range near the static stall angle, where the frequency of the vortex will be equal to the natural frequency and the flutter has the characteristic of self - induced oscillation. when the attack angle is far from the static stall angle, the vortex will have its own frequency, which differs from the natural frequency, and the flutter has the characteristic of forced oscillation
首先研究了二維翼型的古典顫振（小攻角） 、失速顫振（失速攻角）和動力響應問題（大攻角） ，得到以下結論：在靜態失速攻角附近的一定來流速度范圍內，分離渦會發生頻率鎖定現象，分離流的頻率與固有頻率趨于相同，這時的振動呈現自激振動的特點；遠離失速攻角時分離流頻率則擺脫固有頻率的影響，此時的振動具有強迫振動的特點。Experimental data from the towing tank tests show that the hydrofoils give more water - drags on the raft ' s hull, and that the hydrodynamic performance of a ferrying raft will be improved by rational designs of the hydrofoils ' profile, angles of attack as well as the position of hydrofoil on the hull
船模水池中的模型拖曳試驗表明，盡管水翼會增加門橋的水阻力，但只要合理地設計水翼的翼型、攻角和安裝位置，可以改善和提高門橋水動力性能。In spite of these advantages, we should concentrate on how to extend the representation of modes, how to apply to unstructured grids, etc. and when combining pod and saa, it is necessary to know how to represent the shape and how to control the range of seeking and iteration number
但在研究的過程中，我們發現正交分解方法也存在如下問題:如何增強基模態的表達能力，如何將該方法應用於非結構網格的計算等。在利用模擬退火演算法結合解算器進行翼型反設計時，則需要考慮如何表達幾何外形形狀，怎樣控制搜索范圍以及如何減小搜索次數等實際問題。In addition, the dynamic equation of the rotor with trailing edges and the 2 - x actuator has been modeled for analyzing the aerodynamic performance of the rotor. the result of the analysis tells us that the performance of the rotor with trailing edges can get a remarkable improvement
進而研究旋翼動力學模型，將推挽式雙x驅動器模型作為后緣附翼的一種驅動機構，分析旋翼的氣動性能，模擬運算結果表明，后緣附翼智能槳葉在各方面的性能都有顯著的提高。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。4. the influence of reynolds number to aerodynamics and boundary layer is investigated. 5
（ 4 ）研究了雷諾數對翼型氣動力和附面層特性的影響。Along with development of tiltrotor vehicle ’ s research some theoretical productions have been appeared in some project ( aerodynamic behavior of rotor, kinetic behavior of rotor, rotor / wing aerodynamic interactions, etc. ). in order to carry on further research and experimentation of these project, national - defence science and technology helicopter rotor kinetic lab of our school begin to building tiltrotor model bench. base on need of this bench, this paper study / design pitch control system on it
隨著對傾轉旋翼飛行器的深入研究，傾轉旋翼的氣動特性、動力學特性、旋翼/機身間的氣動干擾等課題方面已有一定的理論成果出現。為了對這些課題進行深入研究和試驗驗證，我校直升機旋翼動力學國防科技重點實驗室著手建造了傾轉旋翼模型實驗臺。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。Based on the cavitation chart it can be seen that the charging air with appropriate parameters on blade surface is efficient and feasible for improving the cavitation performance of propeller blades
根據翼型在充氣前後的壓力分佈，確定空泡斗的變化，從而可以認定按適當參數提供的二相流對于擴大空泡斗，以改善螺旋槳空泡性能是有益的和可行的。Numerical simulation shows that, at small and medium c, multi - slot circulation control can increase the lift of the airfoil and reduce the amount of the energy expense, and that it can improve the aerodynamic performance of cca at higher mach numbers by avoiding the “ compressibility stall ”
結果表明，多噴口環量控制方法可以在中、小c吹氣時提高翼型的升力和減小能耗，並能改善環量控制翼型在較高來流馬赫數下的氣動性能，避免「壓縮性失速」 。The main numerical method of this code is coming from scheme ( jameson, schimit and turkel ) : using cell - centered finite volume method as spatial discretization tools, and a system of ordinary differential equations for time variable is obtained, which is solved by utilizing five - step runge - kutta scheme as time marching method, introducing artificial dissipation to damp high frequency oscillations near the shock and stagnation point
本論文採用歐拉方程作為控制方程，利用中心有限體積法進行空間離散，得到對時間變量的常微分方程組，採用龍格庫塔多步法進行時間積分，加入人工粘性以消除激波和駐點附近的壓力振蕩等方法來對naca0012翼型的實際流動進行并行數值模擬。With it s old name as : shandong xinda trading co., ltd., was established in 1998, specialized in the issuing and making of areoboat, remote controllable umbrella, remote controllable tri - angle wing, motivated hot air balloon, large scale advertising plan and undertake the photo making by air
原名山東省信達商貿有限公司，成立於1998年，專業從事飛艇遙控動力傘遙控三角翼，動力熱氣球大型廣告飛機等空中飛行廣告的發布與製作，並承攬空中航拍業務。With panel method and finite difference method, the matching of flow parameters on the boundary between viscous and potential flow can be carried out for the two - phase flow on blade surface
本文以naca4412和naca0012兩種翼型為例，通過壓力分佈計算以及同試驗數據的比較分析表明，面元法可以給出更高的精度。We studied four eddy viscosity models ( evm ) and three nonlinear easm models in detail. the two - equation turbulence models are validated through simulating the flow fields over flat plate, airfoils and onera m6 wing. the capabilities of different turbulence models are accessed in this study
加入兩方程湍流模型后，通過對平板、翼型、 oneram6機翼等繞流流場的數值計算，驗證了加入的各湍流模型的準確性，測試了它們對不同湍流流場的預測能力。Attaching mesh generation sources to the moving boundary allows a reasonable mesh distribution after remeshing. quadtree data structure is used to accelerate the searching operation during interpolation. results of mesh deforming about a rotating airfoil show that the new spring analogy greatly improves the deforming ability and mesh quality without lowering the efficiency
以偏轉翼型動網格為例驗證了網格變形技術，結果表明：改進后的彈簧近似方法在保持原有高效率的同時，大大提高了網格變形能力和變形后網格質量。分享友人