高壓風洞 的英文怎麼說

中文拼音 [gāoyāfēngdòng]
高壓風洞 英文
compressed air tunnel
  • 高 : Ⅰ形容詞1 （從下向上距離大; 離地面遠） tall; high 2 （在一般標準或平均程度之上; 等級在上的） above...
  • 壓 : 壓構詞成分。
  • 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
  • 高壓 : 1 （殘酷迫害; 極度壓制） high handed 2 [氣象學] （高氣壓） high pressure3 （高電壓） high tension...
  • 風洞 : [航空] wind tunnel; air tunnel; whirl tube; wind tunnel plant; flume
  1. Nf - 6 wind tunnel is a pressurizing, continuous, high - speed and return - flow aerofoil wind tunnel

    Nf - 6風洞是一座由軸流式壓縮機驅動的增壓、連續、高速迴流式翼型風洞。
  2. Pressurizing, continuous and transonic wind tunnel is the first one in our country, and it is the world ' s first class tremendous high - speed aerofoil wind

    增壓連續式跨音速風洞在我國尚屬首例，是具有國際先進水平的大型高速翼型風洞。
  3. Compressibility effects are investigated with highspeed models in high-speed tunnels.

    壓縮性影響需用高速模型在高速風洞中試驗。
  4. This text studied the mutually interference influences to the aerodynamic force of irregular shape base on analysis using wind force and wind pressure data of super high buildings model obtained by wind tunnel tests, and provided reference to designer and expurgator on building code

    本文以超高層建築剛性模型的高頻天平測力風洞試驗數據和表面測壓風洞試驗數據為依據，研究了復雜外形建築的風力和高層建築相互干擾對風力影響，供設計者及規范修訂時參考。
  5. Hypersonic propulsion test facility is important for the scramjet ground tests

    摘要高超聲速推進風洞是進行超燃沖壓發動機模型地面模擬的重要試驗設備。
  6. The analysis of the repeated test data shows the maximum deviation of air drag coefficient is less than 0. 88 % and the deviation of the most surface pressure data is within 1 %, it illustrates the test data is reliable

    重復試驗的數據分析表明，空氣阻力系數數據的最大偏差小於0 . 88 ，絕大部分測壓試驗數據的偏差均在1以內，這說明客車模型風洞試驗數據的精度較高。
  7. It is for the first time in domestic wind tunnel experiment that to adopt high voltage transducer to rebuild adjusting system of flow field of large - scale wind tunnel

    採用高壓變頻器來改造大型風洞的流場調節系統，在國內風洞業界還是首次。
  8. 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。
  9. In this paper i was in virtue of the fluent software, set up the geometrical model of jin ’ ao mansion and adjacent buildings, used non - equilibrium wall functions to deal with the problem which come from the near wall, used realizable k - turbulent model to simulate the steady flow around 3d high - rise buildings, we can get the distribution of mean wind pressure coefficient of the surface of jin ’ ao mansion and five aerodynamics components. they were compared with the data from the wind tunnel test, we found out the distance between the result of the wind tunnel test and numerical simulation in the acceptable range

    本文以fluent軟體為平臺，建立金奧大廈及其周邊建築的計算幾何模型，近壁區採用非平衡壁面函數法處理，運用基於雷諾時均的realizablek -湍流模型進行高層建築三維定常風場數值模擬，獲得金奧大廈表面時均風壓系數分佈及基底五分量氣動力，並和風洞測壓試驗的結果及風壓系數積分計算的基底五分量氣動力相比較，發現兩者之間的差異在可接受的范圍之內。
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