風洞實驗模型 的英文怎麼說

中文拼音 [fēngdòngshíyànmóxíng]
風洞實驗模型 英文
wind-tunnel model
  • 風 : Ⅰ名詞1 （空氣流動） wind 2 （風氣; 風俗） practice; atmosphere; custom 3 （景象） scene; view 4 ...
  • 洞 : Ⅰ名詞（物體上穿通的或凹入較深的部分; 窟窿; 洞穴） hole; cavity Ⅱ形容詞（深遠; 透徹） profound; thorough; clear
  • 實 : Ⅰ形容詞1 （內部完全填滿 沒有空隙） solid 2 （真實; 實在） true; real; honest Ⅱ名詞1 （實際; 事實...
  • 驗 : 動詞1. （察看; 查考） examine; check; test 2. （產生預期的效果） prove effective; produce the expected result
  • 模 : 模名詞1. （模子） mould; pattern; matrix 2. （姓氏） a surname
  • 風洞 : [航空] wind tunnel; air tunnel; whirl tube; wind tunnel plant; flume
  • 模型 : 1 （仿製實物） model; pattern 2 （制砂型的工具） mould; pattern3 （模子） model set; mould patter...
  1. This paper adopts linear interpolation to deal with data of wind tunnel experiment for sample uav and realizes modeling and simulation of the sample uav with c language in common aerodynamics and moment coefficient

    本文採用線性插值處理樣例無人機風洞試驗數據，採用正常情況下的氣動力及力矩系數數學模型，並用c語言實現樣例無人機建模與模擬。
  2. Fluid experiment ; buff body aerodynamics ; wind engineering ; wind loading on buildings and structures ; modeling wind in an atmospheric boundary wind tunnel ; pedestrian - level wind environment ; wind effects on the efficiency of air - cooled condenser in a large power plant

    實驗流體力學，鈍體空氣動力學，風工程， 、建築物和結構物的風荷載研究，大氣邊界層風洞模擬，行人高度風環境，大型電站空冷系統風效應風洞模擬。
  3. According to the requirements of propeller aerocraft model test in wind tunnel, specifications of the driven motor is presented by aerodynamic analysis, and a short - term operated high power density three - phase induction motor is developed with reasonably designing the motor, such as electromagnetism load, heat checkout and high - efficiency heat exchanger

    摘要針對螺旋槳飛機模型帶動力風洞實驗要求，通過氣動性能分析提出驅動電機的技術指標，在滿足結構約束的條件下，通過合理設計電機的電磁負荷、校核發熱、採用高效冷卻裝置等，研製出短時工作制高功率密度三相異步電機。
  4. Using emended gauss diffusion mode, taking wind erosion modulus as the ground oil pollutant sources, dust and oil pollutant quantity in air and polluting load in water were calculated, a relative model was founded

    本文以土壤侵蝕的風洞實驗求得污染源源強，採用高斯模式對地表風蝕作用的傳輸量進行估算，進而對石油開發區落油通過大氣傳輸途徑對區域水環境（博斯騰湖）的影響進行了預測，建立了相應的模型。
  5. Based on the date of full - scale measurements, modeling wind tunnel tests and theoretical researches of the wind loads on low - rise buildings available, involved the date of the wind tunnel test and computational numerical simulation fulfilled in this paper, the effects of wind loads on low - rise buildings have been studied systematicaly and extensively. it reveled properly the principle of the changes of the surface mean pressures, local pressures, and fluctuating pressures with the building geometry, roof type and slope, wind direction, eave configuration, cladding system, and dominate openings

    本文根據國內外有關低層房屋風荷載的全尺寸實測、模型風洞試驗及其理論方面的研究，包括本文進行的低層房屋屋面風壓分佈的風洞模型試驗和計算機數值模擬計算，對低層房屋的風荷載特性進行了系統而深入的研究，較好地揭示了低層房屋表面的平均風壓、局部風壓和壓力的波動隨房屋的幾何尺寸、屋面形式、屋面坡度、風向角、檐口構造、覆面材料和門窗開洞而變化的特點和規律。
  6. Wind tunnel experiment on the model of the chinese national grand theatre

    中國國家大劇院模型風荷載風洞實驗
  7. As the first successful experiment which has been conducted in china to test the unsteady aerodynamic forces in wind tunnel, the feasibility of the method is proved through numerous tests and abundant practice

    首次在國內成功實現了在風洞中測試橋梁節段模型顫振導數的強迫振動法，並通過大量的試驗驗證了本測試裝置的可靠性。
  8. The demonstration of heat - transfer measuring techniques and prospect of infrared thermal mapping techniques, main parts and performance indexes of a infrared camera, functional blocks and implementation of infrared processing software, experimental facility and measuring system of the wind tunnel has been made. the model emittance was experimentally determined and the three methods correcting directional emittance were compared. those problems of the infinite - slab model thickness and constant wall heat rates hypothesis, the determination of adiabatic wall temperature were discussed in a 1 - d heat conduction analysis

    本文對紅外熱圖測熱技術與應用前景、紅外熱像儀主要部件與性能指標、紅外測熱數據處理軟體功能模塊與實現、風洞試驗設備與測量系統等進行了論述，測量了模型表面發射率並對發射率隨極角變化的三種修正方法進行了對比，對一維熱傳導分析中模型壁厚半無限假設、壁面熱流定常假設、絕熱壁溫選取等進行了探討。
  9. In this thesis, hypersonic sidewall compression inlet ' s self - starting characteristics are numerical simulated and tested. with increasing mach number of inflow gradually, the hypersonic sidewall compression inlets can self - start. compared with the hypersonic sidewall compression inlet starting directly, characteristics are different. moving cowl, decreasing interior contraction ratio also can realize the hypersonic sidewall compression inlet ' s self - starting because of separation bubble on sidewall spilling out

    其次，在數值模擬結果的基礎上，設計了實驗模型和裝置並在馬赫3 . 85的風洞中進行了移動唇口板減小內收縮比實現側壓式進氣道自起動的風洞實驗，驗證了數值模擬的結果。
  10. Especially, the technique proposed here can be expanded to the flutter test with variable speed. the related software is developed on labview for windows

    並通過數值模擬和某型飛機氣彈模型低速風洞顫振試驗驗證了方案的有效性、可靠性和工程實用性。
  11. In chapter 4, the aeroelastic model of the whole test rig is first established by using jones ’ s approximation of theodorsen ’ s unsteady aerodynamics load. then, the numerical simulations and wind tunnel experiments for the sub - optimal flutter suppression of the airfoil model are presented

    數值模擬和風洞實驗研究表明，以超聲電機為控制面作動器可以有效地抑制翼段模型的顫振，顫振臨界速度提高了13 . 4 % ，數值模擬和風洞實驗結果基本吻合。
  12. For simulating the radial static pressure gradient behind the true turbine guide cascade in low speed wind tunnel with annular cascade, the backboards were placed in the downstream field of the guide model cascade of the low - pressure stage of a turbine, and the effects of the types and positions of the backboards on the outlet flow field of the model cascade were experimentally researched

    為在環形葉柵低速風洞實驗中模擬實際渦輪級靜葉后徑向壓力梯度，在某型渦輪低壓級靜葉的下游流場設置了擋板，實驗研究了擋板形式及設置位置對靜葉出口流場的影響。
  13. Simulation study on resistances to wind erosion of new polymer material in sand fixation

    新型高分子材料固沙抗風蝕的風洞模擬實驗
  14. These landslides go with fluidization peculiarity different degree in course of their motion, and their speed and distance increase several times because of the fiuidization, thereby the disaster area greatly broaden. on the base of above, the paper studies systematically the fluidization of large high - speed rockslides in all its aspects : analyzed the aerodynamic effect in the short - range on the base of the wind turmel experiment, studied the effect of falling into pieces when landslides collides mountain ; studied the accelerating effect through high - speed collide experiment of landslides model ; and the paper reappear the overall process including set - out, collide in the short range, debris flow in the long - range of touzhai large landslide via distinct element method ( dem ), studied the flow law and equation of different type of debris flow resulted from large landslide. as a sample to apply, the paper analyzed fluidization mechanism of touzhai landslide

    基於這一點，本文對大型高速巖質滑坡的流體化現象進行了全面而系統的研究：通過風洞模型實驗，研究了大型高速滑坡凌空飛行階段的空氣動力學效應，研究了飛行中滑坡巖體在與途中不動山體發塵碰撞時的解體破碎效應，通過滑坡巖體高速碰撞模型實驗研究了滑坡巖體解體破碎後部分巖體的加速運動效應，並應用離散單元法再現了雲南頭寨溝大型滑坡啟動高速、近程碰撞、遠程碎屑流運動的全過程，研究了巖體解體破碎后形成不同類型碎屑流的運動規律及運動方程，並對頭寨滑坡流體化運動機理進行了實例分析，取得了以下主要結論和成果： （ 1 ）對于大型高速滑坡，大多在啟程活動階段已獲得了高速，這使得這類滑坡在其離開剪出口之後以凌空飛行的形式向前運動，在其飛行過程中，滑坡巖體與空氣強烈作用，並產生空氣動力學效應，滑坡巖體在因碰撞而產生的解體破碎效應及部分巖體的加速運動效應的作用下，在遠程活動階段，以高速碎屑流的形式向前運動。
  15. The main results of the wind tunnel experiment on the 1 200 model of the chinese national grand theatre were introduced. at first, the wind pressure distributions of its semi - ellipsoidal surface in an atmospheric boundary layer flow were simulated, and the effect of the surface roughness was researched. the results indicated a reasonable regularity of its wind loading in various wind directions. on the problem of the environmental influence, it demonstrated that there existed a great effect for the pressure distribution of the great theatre when the grand hall is at east

    介紹中國國家大劇院模型表面風荷載的風洞實驗結果。首先對它的半橢球表面在大氣邊界層中的風壓分佈及增加表面粗糙度的影響進行研究，實驗結果表明在不同風向下它的風荷載具有很好的規律性。有環境影響的對比實驗結果表明人民大會堂對大劇院的風荷載有較大的影響。
  16. Physical modeling of atmospheric boundary layer wind tunnel experiment

    大氣邊界層風洞實驗的物理模型
  17. 2. the model experiment aimed at the aerodynamic effect of large high - speed landslides has been accomplished in wind tunnel laboratory for the first time. on the base of testing research, the paper studies different factor which influence the aerodynaxnic effect of flying 1andslide, and numerically simulates the aerodynamic effect with the help of the hydrodynamics finite element

    （ 2 ）首次在風洞實驗室進行了針對大型高速滑坡凌空飛行階段空氣動力學效應的模型實驗，研究了影響飛行滑坡巖體空氣動力學效應的不同因素；應用流體力學有限單元法對飛行滑坡巖體的空氣動力學效應進行了數值模擬。
  18. The parameters of the actuator model are estimated via the tests under sweep sinusoidal excitation. the effectiveness of the model is validated through wind tunnel tests. chapter 3 presents the design of the test rig and the measurement / control system software

    通過掃頻實驗和非線性最小二乘法進行參數識別，得到傳遞函數模型中各參數的值，並通過和風洞實驗驗證了模型的有效性。
  19. Using the developed computer program the wind flow around a cubic building model, a rectangle - section tall building and a gable - roof building are first numerical predicted, respectively. in the prediction the single - area and multi - area grid refinement approaches are respectively used and the numerical results are compared with the wind - tunnel test results and the numerical results without grid refinement obtained by other researchers. this indicates that the proposed nonstaggered grid and refinement scheme is not only valid and easy to be car

    採用編制的計算程序首先對一立方體建築模型、一矩形截面高層建築和一雙坡屋面建築的繞流風場進行了模擬計算，分別採用單域和多域加密方案對建築周圍的網格實施了局部加密，數值模擬結果與風洞試驗結果以及其他研究者的非加密計算結果進行了比較。
  20. First, being based upon kalman filter, extended kalman filter formulas was established ; second, with using extended kalman filter in non - linear dynamics system maximum likelihood identification method, the self - contained formulas of estimating parameter was established ; third, according to the air layout of the missle, the aerodynamic parameters identification calculating model was gained, with applying to the non - linear dynamics system maximum likelihood identification method ; finally, with using the calculating model, the aerodynamic parameters were gained. the results which were gained from the calulating model were almost consistent with which were gained from the wind tunnel experiment. thus, it was viable to use the method to estimate the aerodynamic parameters

    首先，以卡爾曼濾波為基礎，將其推廣于非線性動力學系統，建立了廣義卡爾曼濾波算式；其次，把廣義卡爾曼濾波算式應用於非線性動力學系統最大似然演算法和非線性動力學系統最大似然遞推演算法中，建立了各自的參數估計完備算式；再其次，以所建立的傾斜穩定導彈空間運動數學模型為基礎，根據該導彈的氣動布局，推導並建立了該導彈空間運動數學模型，將最大似然遞推演算法應用其中，建立了導彈氣動力參數辨識的數學模型；最後，利用該模型，估算出了氣動力參數，所得結果與風洞實驗數據基本吻合，從而認為採用此方法是可行的。
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