stagnation point 中文意思是什麼

stagnation point 解釋
停滯點
  • stagnation : n. 1. 停滯，不流，不動；滯止。2. 蕭條。3. 遲鈍。
  • point : n 1 尖頭，尖端；尖頭器具；〈美國〉筆尖；接種針，雕刻針，編織針；小岬，小地角；【拳擊】下巴。2 【...
  1. Standard test method for calculation of stagnation enthalpy from heat transfer theory and experimental measurements of stagnation - point heat transfer and pressure

    通過臨界點傳熱與壓力的熱傳遞理論和實驗測量來計算臨界熱函的標準試驗方法
  2. The quarter - point increase marked an end to the rich world ' s longest economic stagnation since the great depression

    將利率提高0 . 25 %標志著這個富裕國家結束了它自大蕭條以來歷時最長的經濟停滯。
  3. The key factors affecting the stagnation point position of l - type pipeline section are the setting position of bellows type expansion joint and the bend angle degree

    影響水平轉角管段駐點位置的主要因素為波紋管補償器設置位置、彎頭角度。
  4. The calculation of stagnation point position of straight pipeline section with both movable ends and l - type pipeline section with bend at one end and bellows type expansion joint at other end is discussed

    摘要探討了兩側為活動端的直管段及一側活動端為彎頭，而另一側活動端為波紋管補償器的水平轉角管段駐點位置的計算。
  5. Abstract : approximate methods for calculating aerodynamic heating rates on space shuttles are discussed. various methods are given for predicting the heating rate at axisymmetric stagnation points, general three dimensional stagnationpoints and the leading edge stagnation point of wings. numerous laminar and turbulent heating techniques for flat plates and cones are analyzed and compared. a brief review of some methods is presented to predict heating rate for winward centerline and lateral direction off the symmetry plane. the results show that the methods are simpler and can guarantee enought precision for predicting aerodynamic heating environment of space shuttles

    文摘:介紹了國內外預測航天飛機氣動加熱的工程計算方法.給出了軸對稱、非軸對稱和機翼前緣等各種外形駐點熱流密度的計算，分析和比較了平板、錐體的層流和湍流熱流密度計算的各種方法，概述了航天飛機迎風面中心線和離開中心線橫向熱流密度的計算.計算結果表明，本文方法用在航天飛機氣動熱環境初步設計中比較簡單並且有足夠精度
  6. The main numerical method of this code is coming from scheme ( jameson, schimit and turkel ) : using cell - centered finite volume method as spatial discretization tools, and a system of ordinary differential equations for time variable is obtained, which is solved by utilizing five - step runge - kutta scheme as time marching method, introducing artificial dissipation to damp high frequency oscillations near the shock and stagnation point

    本論文採用歐拉方程作為控制方程，利用中心有限體積法進行空間離散，得到對時間變量的常微分方程組，採用龍格庫塔多步法進行時間積分，加入人工粘性以消除激波和駐點附近的壓力振蕩等方法來對naca0012翼型的實際流動進行并行數值模擬。
  7. Flow noise scaling at the stagnation point of an axisymmetric body

    回轉體駐點處的流噪聲相似律
  8. The results show that, for reynolds number of 4400 ~ 23800, heat transfer coefficients at stagnation point always increase with the increasement of reynolds number ; the average deviation of heat transfer coefficients at stagnation point from published results is about 10. 8 %, which shows the system is reliable for temperature measurement

    實驗結果表明，在re = 4400 28300范圍內，駐點區換熱系數隨雷諾數的增大而增大；駐點區換熱系數與前人的實驗結果相比平均誤差10 . 8 ，實驗系統具有很好的可靠性。
  9. It is found that, the heat transfer coefficients in the area after at stagnation point is higher than that of common jetting although the heat transfer coefficients are smaller at stagnation point, and, comparing to common jetting, rotary jetting contributes to the even distribution of heat transfer coefficients near stagnation point

    結果表明，盡管旋轉射流的努謝爾特數在駐點附近低於普通射流的努謝爾特數，但在壁面射流區高於普通射流的努謝爾特數。與普通射流相比，旋轉射流導致駐點附近區域的換熱特性趨于均勻化。
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