pressure recovery coefficient 中文意思是什麼

pressure recovery coefficient 解釋
壓力恢復系數
  • pressure : n 1 壓；按；擠；榨。2 【物理學】壓力，壓強；大氣壓力；電壓。3 精神壓力，政治[經濟、輿論等]壓力。4...
  • recovery : n. 1. 重獲；復得；恢復，收回，回收。2. 還原，復原；痊癒；蘇生；矯正。3. 回縮。4. 填地。5. 【法律】勝訴。
  • coefficient : adj. 共同作用的。n. 1. 共同作用；協同因素。2. 【數，物】系數，率；程度。
  1. Using the opened thermosiphon of 38x3 as experimental element and water as working fluid, the characteristics of dynamic low load boiling, stable severe boiling heat transfer coefficient and critical heat flux are gotten for the opened thermosiphon at the pressure of 0. 02 - 0. 1mpa and 0. 1 - 0. 8mpa respectively, which makes up the drawback that the opened thermisiphon has not yet accurate boiling heat transfer relationship formulas. by means of experimental results, an opened thermisiphon waste heat recovery boiler is designed for the high temperature gases that the positi e electrode copper refining furnace exhaust, which overcomes effectively the drawback of short life, little capacity and unable to inspect that the closed steel - water thermosion has

    本文以工程上常用的38 3的開口封底為實驗元件，以水為工質，對開啟式熱管內的動態低負荷沸騰、穩態旺盛沸騰及臨界沸騰特性進行系統的可視化實驗研究，實驗壓力為0 . 02 0 . 8mpa ，實驗得出了38 3的開口封底管在工作壓力為0 . 02 0 . 8mpa和0 . 1 0 . 8mpa下的管內沸騰傳熱系數及臨界熱負荷計算關聯式，彌補了開口封底管? ?這一新型傳熱元件尚無準確的沸騰換熱關聯式的缺陷。
  2. On the basis of these results, the relations of total - pressure recovery coefficient or flow coefficient and flight mach number, angle of attack and the second movable wedge angle of the inlet have been founded by hypersurface fitting, then the mathematical model of the inlet is established

    根據流場計算結果並利用超曲面擬合方法建立了進氣道總壓恢復系數、流量系數與飛行馬赫數、進氣道攻角及二級可調斜板角度之間的關系，由此得到了二元混壓式超聲速進氣道數學模型。
  3. The results prove that : ( 1 ) when the mach number of the flow at the exit increases, the total pressure recovery decreases, and the circular steady total pressure distortion coefficient, turbulence intensity and synthesis distortion increase

    研究結果表明： （ 1 ）地面工作狀態下，隨著出口馬赫數的增加，蛇形進氣道出口截面的總壓恢復系數不斷下降，而穩態周向畸變指數、紊流度和綜合畸變指數均上升，穩態徑向畸變指數變化不大。
  4. When the serpentine inlet is running at the exit mach number ma ( subscript e ) = 0. 45, the total pressure recovery coefficient equals 0. 90, and synthesis distortion equals 13. 85 %

    本研究的蛇形進氣道在出口馬赫數為0 . 45時，總壓恢復系數為0 . 90 ，綜合畸變指數為13 . 85 % ，總壓恢復較低，畸變較大，超出了一般航空發動機的承受范圍。
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