翼型數據 的英文怎麼說
中文拼音 [yìxíngshǔjù]
翼型數據
英文
airfoil data-
In order to verify the accuracy, credence and effectiveness of the unstructured overset grid algorithm, steady and unsteady flow field of naca0012 airfoil are simulated. the unsteady flow field is caused by the oscillation of the airfoil. the two computational results are both compatible well with the experimental data
為了驗證非結構重疊網格方法的正確性、可靠性和有效性，本文對基於非結構重疊網格的naca0012翼型的定常流場以及簡諧振蕩的非定常流場進行了數值模擬，均取得了與實驗數據符合良好的結果。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。Some typical schemes are implemented via this data structure ( loop subdivision, catmull - clark subdivision, do - sabin subdivision, hybrid subdivision, adaptive subdivision ). the technique of opengl is utilized to accomplish some basic operations, such as rotation, zoom, pan, pick and so on. finally the algorithms studied by our research group are integrated, and a prototype system based on subdivision surface is developed
（ 4 ）改進了適合於曲面細分的的翼邊數據結構，並實現了典型的細分演算法（ loop細分、 catmullclark細分、 doo - sabin細分、混合細分、自適應細分） ；採用opengl技術實現了旋轉、縮放、平移、拾取等圖形的基本幾何操作；最後將本課題組研究成果加以集成，開發了一個基於細分曲面的原型系統。On the base of the numerical simulation of unsteady viscous flows, the characters of the static aeroelastics and flutter for the wings are researched. some examples, simulating the steady and unsteady transonic ( and subsonic ) viscous flows around onera m6 wing, are given in this paper
以oneram6機翼為算例，分別對其亞、跨音速定常及非定常粘性繞流狀態進行了數值模擬，並運用b - l和j - k兩種湍流模型計算結果和實驗數據進行了對比。According to the force balance equations, the values and distributions of bond stress between steel shape flange and concrete in eccentric loading columns were established by statistically regression with experiment data. and the influence of the factors such as relative eccentricity e0 / h, the slenderness ratio l0 / h on the bond - slip properties was analyzed
利用力的平衡方程，通過對試驗數據統計回歸，得到了偏壓柱型鋼兩側翼緣與混凝土的粘結應力的大小及分佈規律，並分析了偏壓柱長細比、偏心距對其的影響。Several icing parameters were imported to calculate the change of drag coefficient and typical derivatives between clean aircraft and iced aircraft, and the aircraft flight envelope change of iced and un - iced situation was computed, and the small disturbance flight dynamics model was modified to study the effect of the ice accretion on the aircraft dynamics by importing the ice parameter to it, and the longitudinal and lateral stability and the elevator, aileron and rudder step response were also studied and simulated
根據這些參數計算了飛機結冰后阻力系數以及典型氣動導數的變化，並計算了結冰前後飛機的飛行包線；同時對結冰前後飛機的縱向、橫側動穩定性以及升降舵、副翼和方向舵階躍操縱響應進行模擬計算。2. an unsteady, nonlinear state - space airfoil aerodynamics model was developed with onera dynamic stall model
對於後行槳葉的動態失速行為，引入了對翼型實驗數據不敏感，並也具有狀態空間形式的onera動態失速模型。20 src eccentric loading specimens were designed taking the relative eccentricity e0 / h the slendemess ratio 10 / h as the factors. according to the mechanical behavior of eccentric loading columns, unidirectional embedded electronic steel - concrete slip transfers and double - directional embedded electronic steel - concrete slip transfers were respectively placed inside these 20 specimens and electronic strain gauges were also installed on the steel shape flanges webs and concrete. the change of the mechanical behavior and interior slip of the 20 specimens in the whole process of loading was fully observed
設計了以長細比、偏心距為主要參數的20個偏壓柱試件，根據偏壓柱的受力特性，在試件中分別放置了單向內置式鋼?混凝土電子滑移傳感器和雙向內置式鋼?混凝土電子滑移傳感器，並分別在型鋼翼緣、腹板和混凝土上布置了電子應變片，對試驗柱在受荷全過程的受力性能、和內部滑移的變化進行了細致的觀察。At the end of the experiment, we reconstructed the subsystem of second air measuring, i. e. we used airfoil measuring equipment as a replacement of original equipment of flute pipe. we also demarcated the velocities of spouts of burner which can deal with correlative data, and which can provide some help for operation
最後又對監測系統二次風測量子系統進行改造，將原笛型管裝置修復為機翼測風裝置，對傳感器進行差壓標定;在爐內噴口處標定速度，將數據進行處理，提供給熱工控制顯示用，對運行調整提供了幫助。So, when we get the dates of stress and distortion of wing ' s model structure, which have been calculated by computer, we can simulate the dates of the real wing ' s structure, which we will get through stress sensors and distortion sensors. when we transmit those dates to the center computer through remote wireless transmission devices, the computer will analyze those dates according as scientific fault criterion. so we can carry out the remote real - time health monitoring for wing ' s structure
這樣，我們讀取計算出的機翼結構模型在受力時的應力、變形值就可以模擬出在採用實體機翼作為研究對象時應力、變形傳感器傳回的數據，把這些數據通過遠程無線數據傳輸設備傳到數據處理計算機上採用科學的故障判據對這些數據進行處理就可以實現對機翼結構的實時遠程健康監控。In order to set up the dynamic model of swimming micro robot, this dissertation builds up the statics model and analyses the micro motion amplifying performance of micro robot mechanism, builds up the vibration model of micro robot and analyses the vibrating performance without and with damp, researches the propelling force of driven wing and the resistance of micro robot in liquid based on the theory of flat board resisting stream, builds up the dynamic model of swimming micro robot for the first time in nation and analyses its swimming performance which is influenced by driving signal frequency, amplifying performance of main machanism, area of driven wing, character of fluid and so on. this dissertation manufactures the micro robot and sets up the experimental environment and tests the amplifying effect and the vibrating performance
本文建立了主體機構靜力學模型，研究了主體機構的結構參數對微位移放大性能的影響；建立了主體機構振動模型，研究了主體機構在無液體阻尼和有液體阻尼情況下的振動特性；根據流體力學平板繞流理論，研究了驅動翼產生的推進力和微機器人在流體中受到的阻力；在此基礎上國內首次建立了泳動微機器人的動力學模型，並對模型進行了深入的研究，詳細闡明了驅動信號頻率、主體機構放大性能、主體機構振動特性、驅動翼面積、液體性質等因素對微機器人泳動特性的影響。In the transversal vibration test of the steel supporting post on the flange of qinshen railway bridge, the practical techniques of instrument selection, the provision of static eliminater and the way of data sampling are mainly discussed
摘要針對秦沈線橋上翼緣板接觸網鋼柱的橫向振動測試，著重論述了儀器的選型、抗靜電干擾措施以及數據採集中的具體技術。Abstract : a new method, collaborative allocation ( ca ), is proposed to solve the large - scale optimum allocation problem in aircraft conceptual design. according to the characteristics of optimum allocation in aircraft conceptual design. the principle and mathematical model of ca are established. the optimum allocation problem is decomposed into one main optimization problem and several sub - optimization problems. a group of design requirements for subsystems are provided by the main system respectively, and the subsystems execute their own optimizations or further provide the detailed design requirements to the bottom components of aircraft, such as spars, ribs and skins, etc. the subsystems minimize the discrepancy between their own local variables and the corresponding allocated values, and then return the optimization results to main optimization. the main optimization is performed to reallocate the design requirements for improving the integration performance and progressing toward the compatibilities among subsystems. ca provides the general optimum allocation architecture and is easy to be carried out. furthermore, the concurrent computation can also be realized. two examples of optimum reliability allocation are used to describe the implementation procedure of ca for two - level allocation and three - level allocation respectively, and to validate preliminarily its correctness and effectiveness. it is shown that the developed method can be successfully used in optimum allocation of design requirements. then taking weight requirement allocation as example, the mathematical model and solution procedure for collaborative allocation of design requirements in aircraft conceptual design are briefly depicted
文摘:探討了一種新的設計指標最優分配方法- -協同分配法，用於處理飛機頂層設計中的大規模設計指標最優分配問題.分析了飛機頂層設計中的設計指標最優分配特徵，據此給出了協同法的原理並建立了數學模型.協同法按設計指標分配關系將最優分配問題分解為主系統優化和子系統優化，主優化對子系統設計指標進行最優分配，子優化以最小化分配設計指標值與期望設計指標值之間的差異為目標，進行子系統最優設計，或對底層元件（如飛機翼梁、翼肋和翼盒等）進行設計指標最優分配，並把最優解信息反饋給主優化.主優化通過子優化最優解信息構成的一致性約束協調分配量，提高系統整體性能，並重新給出分配方案.主系統與子系統反復協調，直到得到設計指標最優分配方案.兩層可靠度指標分配算例初步驗證了本文方法的正確性與可行性，三層可靠度指標分配算例證明了本文方法的有效性.最後，以重量指標分配為例，簡要敘述了針對飛機頂層設計中設計指標協同分配的數學模型和求解思路A new method, collaborative allocation ( ca ), is proposed to solve the large - scale optimum allocation problem in aircraft conceptual design. according to the characteristics of optimum allocation in aircraft conceptual design. the principle and mathematical model of ca are established. the optimum allocation problem is decomposed into one main optimization problem and several sub - optimization problems. a group of design requirements for subsystems are provided by the main system respectively, and the subsystems execute their own optimizations or further provide the detailed design requirements to the bottom components of aircraft, such as spars, ribs and skins, etc. the subsystems minimize the discrepancy between their own local variables and the corresponding allocated values, and then return the optimization results to main optimization. the main optimization is performed to reallocate the design requirements for improving the integration performance and progressing toward the compatibilities among subsystems. ca provides the general optimum allocation architecture and is easy to be carried out. furthermore, the concurrent computation can also be realized. two examples of optimum reliability allocation are used to describe the implementation procedure of ca for two - level allocation and three - level allocation respectively, and to validate preliminarily its correctness and effectiveness. it is shown that the developed method can be successfully used in optimum allocation of design requirements. then taking weight requirement allocation as example, the mathematical model and solution procedure for collaborative allocation of design requirements in aircraft conceptual design are briefly depicted
探討了一種新的設計指標最優分配方法- -協同分配法，用於處理飛機頂層設計中的大規模設計指標最優分配問題.分析了飛機頂層設計中的設計指標最優分配特徵，據此給出了協同法的原理並建立了數學模型.協同法按設計指標分配關系將最優分配問題分解為主系統優化和子系統優化，主優化對子系統設計指標進行最優分配，子優化以最小化分配設計指標值與期望設計指標值之間的差異為目標，進行子系統最優設計，或對底層元件（如飛機翼梁、翼肋和翼盒等）進行設計指標最優分配，並把最優解信息反饋給主優化.主優化通過子優化最優解信息構成的一致性約束協調分配量，提高系統整體性能，並重新給出分配方案.主系統與子系統反復協調，直到得到設計指標最優分配方案.兩層可靠度指標分配算例初步驗證了本文方法的正確性與可行性，三層可靠度指標分配算例證明了本文方法的有效性.最後，以重量指標分配為例，簡要敘述了針對飛機頂層設計中設計指標協同分配的數學模型和求解思路After the data is analyzed, the software of fluent is used to calculate the flowfield. in order to make the calculation results agree with the experimental data, the model of the calculation has been modified based on the results of the experiment data
詳細分析比較旋翼機翼間的氣動干擾試驗數據后，應用fluent軟體進行分析計算，根據試驗結果修正計算模型，使計算結果與試驗結果趨於一致。The three basic steps are as follows : firstly, the flow field is computed. secondly, the droplet trajectory equation is solved in order to determinate the limiting droplet trajectories and local collection coefficient. thirdly, a new iced shape is defined according to ice accretion model
其基本步驟一般分三步：計算物體的繞流流場；求解水滴軌跡方程以確定極限水滴軌跡和收集系數；根據冰增長模型來確定新的結冰翼型形狀。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。Thirdly, the air - air missile ' s model is studied, and set up guided missile motion equations that passes through the area of the down wash. using the preceding down wash distributing data, the fly situation and orbit changes in initial stages of the guided missile launch have been studied
再次，對空空導彈的模型進行了研究，並建立了導彈穿越旋翼下洗區域的運動方程，運用前面的下洗分佈數據，研究了導彈發射最初階段的運動情況和軌跡變化。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。At the same time, this article has carried on the mode test to my school mechanics laboratory cantilever beam structure and the model wing two kind of structures, and particularly researched for the mode test as well as carried on processing to the test data
同時，本文對我校力學實驗室的懸臂梁結構和機翼模型兩種結構進行了模態試驗，並對試驗進行了詳細研究以及對試驗數據進行處理。分享友人