風洞風速計 的英文怎麼說

中文拼音 [fēngdòngfēngsùjì]
風洞風速計 英文
wind tunnel speed gage
  • 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
  • 速 : Ⅰ形容詞（迅速; 快） fast; rapid; quick; speedy Ⅱ名詞1 （速度） speed; velocity 2 （姓氏） a surna...
  • 計 : Ⅰ動詞1 （計算） count; compute; calculate; number 2 （設想; 打算） plan; plot Ⅱ名詞1 （測量或計算...
  • 風洞 : [航空] wind tunnel; air tunnel; whirl tube; wind tunnel plant; flume
  • 風速 : [氣象學] wind [air] speed; wind [air] velocity
  1. Abstract : based on thestatic wind force factors of a tower and on the root - mean - square of the buffetingdisplacement responses of the tower top, which are measured by wind tunnel tests inlaminar and turbulent field respectively, the static and buffeting internal forces of thetower bottom control sections under its design wind speed are obtained by linearsuperposition method and fem

    文摘:基於均勻流和紊流風場中的橋塔模型風洞試驗所測得的橋塔空氣力靜力系數及塔頂抖振響應的位移均方根，採用線性疊加法及有限元法反演，給出設計風速下塔底控制截面的順風向靜風及抖振內力。
  2. The tests were conducted in the hypersonic low density wind tunnel at nominal test conditions of mach 16, stagnation temperature 923k, stagnation pressure 1. 40mpa and 7. 30mpa. heat - transfer data were obtained on a hemisphere model, a sharp cone and a big blunt cone respectively by means of infrared thermal mapping techniques, that of a 0. 5mm thickness blunt cone by virtues of thermocouples. furth ermore, heat - transfer on all those models was calculated with the theoretical method

    最後在名義m _ = 16 、 t _ 0 = 923k 、 p _ 0 = 1 . 40mpa及7 . 30mpa的高超聲速低密度風洞中，利用紅外熱圖技術獲得了半球圓柱、尖錐、大鈍頭三個模型表面熱流分佈，利用薄壁法技術得到了一壁厚為0 . 5mm的鈍錐模型表面的熱流分佈，並通過工程理論方法計算了模型表面的氣動熱，把理論計算結果與上述試驗結果比較，幾者符合得較好。
  3. An efficient wind field simulation technique for wind - induced vibration analysis of long - span bridges is first introduced in this paper ， and the statistic characteristics of the simulated wind field are then discussed on this basis ， the time - domain expressions for the buffeting and self - excited forces acting on long - span bridges are further given a simple and practical method is presented for the non - linear parameter identification involved in the calculation of self - excited forces by using the above theory ， the wind field and aerodynamic forces acting on the hong kong ting kau bridge are obtained the time - domain buffeting response analysis of the bridge shows that the analytic results agree quite well with the experimental ones this indicates that the theory presented in this paper has reached a practical level

    介紹了一種快速高效的用於大跨度橋梁風致振動分析的風場模擬方法，並對模擬風場的統計性質進行了討論和驗證在此基礎上進一步給出了大跨度橋梁抖振力和自激力的時域表達方式，其中針對自激力計算中涉及的參數識別問題，提出了一種簡單實用的非線性參數識別方法本文採用上述理論，獲得了作用於香港汀九大橋上的風場和氣動力，據此對大橋進行的抖振響應時域分析表明，計算結果與風洞試驗結果吻合良好，說明文中述及的這套理論已達到實用的階段
  4. A hypersonic pulse tunnel is designed in this paper, which has multiple running modes based on gun tunnel and shock tube theory

    本文設計了一座具有多種運行方式的高超聲速大型脈沖風洞，該風洞可以採用炮風洞和激波管兩種運行方式。
  5. The code calibration is completed by comparing the numerical results with data from two experiments, one of which is test of a 2 - d hypersonic inlet with internal compression and the other a sidewall compression inlet. good agreement of numerical and experimental results proves the possibility and credibility of the numerical method

    利用國外文獻公布的二維進氣道實驗結果和本課題組側壓式進氣道炮風洞實驗獲得的實驗數據對本文的計算方法進行了校驗，證明了本文所採用的方法應用於高超聲速進氣道計算的可行性和可靠性。
  6. Abstract : in this paper, a principle and method of the speed pulse waveform sampling are introduced. its object is to study an effect of the turning factor on torbulence. test is done in the aerofoil fengwen. on design of the user interface, application of the timer and displaying way of a pape and continuity are specifically discussed. expermental results and analysis is showed at the last

    文摘:以翼型風洞為對象，著重介紹了變湍流度對翼型轉捩因子影響的速度脈動波形採集的原理和方法，重點對波形採集系統用戶界面的設計、定時器的應用、分頁顯示和連續顯示等技術進行了具體介紹，並給出了實驗結果及分析。
  7. The design and computation of the hypersonic nozzle have scientific and practical value to solve these problems

    而高超聲速風洞噴管的設計和計算則對解決這一類問題具有重要的科學意義和實用價值。
  8. The relationship between the load measured by strain method and the load calculated according to flight parameters and the wind tunnel test data has been investigated in this thesis. the result showed that the calculation load based on the flight parameters and wind tunnel test data is acceptable in subsonic speed and gets good agreement, with the load measured by strain method

    本文研究了採用應變法實測載荷和根據飛行實測參數和風洞實驗數據計算載荷之間的關系，研究表明採用飛行實測參數和風洞實驗的數據計算載荷在亞音速范圍內是可行的，與採用應變法實測載荷是吻合的。
  9. Aiming at the structure characteristics of the pipeline system of the existing boiler combustion equipment, the paper work out the new - style air speed measure components via the theory analysis of the existing measure components of all kind of forms and measure theory. and then the paper designs and builds the wind tunnel test - bed to process the test and research of the air speed measure components in order to realize it ' s structure and each characteristic parameter

    針對現有的鍋爐燃燒設備管路系統的結構特點，論文通過對現有的各種形式、測量原理的流量測量裝置的理論分析，設計出新型的風速測量元件，並且設計、建立滿足試驗所需的風洞試驗臺，對風速測量元件的結構及各項特性指標進行試驗研究，完成一次元件的開發工作。
  10. Numerical results are in good agreement with some data and the method and procedure presented in this paper are verified. and then the wing ? flutter characters of a missile wing are numerical simulated with the examples of a missile wing

    以某導彈翼面為算例，對彈翼的亞、跨、超音速的顫振臨界速度進行了數值計算，部分計算結果與風洞計算結果相比較，一致性很好。
  11. Abstract : based onmethods of foreign countries of using wi nd tunnel test and numerical flow simulation, optimum nose a nd tail shapes ofhigh - speed trains are studied to achieve optimum aerodynamic performance so as to efficiently reduce the influence of theaerodynamic phenome na on the train operation and the environment. research results of foreign countr ies are introduced

    文摘:針對國外利用以風洞模型模擬試驗和以流場數值模擬計算為主的方法來尋求高速列車最佳的頭尾部形狀，使列車的綜合氣動性能最佳，從而有效地降低空氣動力學現象對列車運行和周圍環境的影響進行了探討，介紹了國外在此方面取得的主要成果。
  12. Film cooling of the surface of a gas turbine blade was studied in a large - scale low - speed opening wind tunnel according to actual requirement of the design of aero - engine. the surface of a gas turbine blade was cooled by cylindrical holes in the experiment, with the hole number of fifteen in stator and eight in rotor

    應航空發動機設計的要求，在大尺寸低速葉柵傳熱風洞中分別對發動機渦輪導向葉片和動葉表面的氣膜冷卻特性進行了研究，具體研究在不同氣膜孔出流時，在不同主流雷諾數和吹風比情況下葉片表面局部換熱系數的分佈規律。
  13. Using the program the wind fields around several buildings with different body shapes are analyzed. the final results of grid division and refinement are presented. the final wind velocities around the building and wind pressures on the building surface are obtained and also compared with those from the wind runnel test

    採用計算程序對幾種不同體型建築物的流動風場進行了模擬計算，給出了計算區域的網格剖分和加密結果，獲得了離散后的流場的風速和風壓模擬結果，並與風洞試驗結果進行了比較。
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