前駐點線 的英文怎麼說

中文拼音 [qiánzhùdiǎnxiàn]
前駐點線 英文
front attachment line
  • 前 : Ⅰ名詞1 （在正面的） front 2 （次序在先的） first; top 3 （過去的; 較早的） ago; before; preceding...
  • 駐 : 動詞1. （停留） stay; halt; stop 2. （住在執行職務的地方; 設在某地） be stationed; encamp
  • 點 : Ⅰ名詞1 （液體的小滴） drop （of liquid） 2 （細小的痕跡） spot; dot; speck 3 （漢字的筆畫「、」）...
  • 線 : 名詞1 （用絲、棉、金屬等製成的細長的東西） thread; string; wire 2 [數學] （一個點任意移動所構成的...
  • 駐點 : arrest point
  1. The thermal visualizations of jet impingement cooling with single or double row holes inside semi - enclosed channel are measured by using infrared camera and then the impingement cooling heat transfer coefficients are deduced. the effects of flow and geometry parameters on convective heat coefficients are obtained. the results show that : for a single row normal impingement, the impingement cooling effectiveness is enhanced with the increase of impinging reynolds number or the decrease of hole space to diameter ratio, and the best effectiveness is achieved under the jet - to - surface spacing equals to 2 ; when the jet is oblique to the confined wall, the cooling effectiveness is weaken especially under the jet - to - surface spacing ratio is greater than 2 ; for double rows normal impingement cooling, the cooling effectiveness of rear row jet is weaker than the front row under lower impinging reynolds number or bigger jet - to - surface spacing

    對于單排垂直射流，沖擊冷卻效果隨射流雷諾數的增加、孔間距與直徑比的減小而得到提高，沖擊間距比為2時換熱效果最好;沖擊孔中心線向通道封閉一側傾斜后，射流沖擊冷卻的范圍變窄，當沖擊間距比大於2時駐點區的對流換熱能力明顯降低;對于雙排沖擊射流，孔排間距與直徑比的增加使沖擊冷卻范圍變大，但在兩排孔之間區域的對流換熱系數有所下降;在較小的沖擊射流雷諾數和較大的沖擊間距比下，後排射流的沖擊換熱效果要遜於前排射流。
  2. 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
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