駐點表面 的英文怎麼說

中文拼音 [zhùdiǎnbiǎomiàn]
駐點表面 英文
stagnation surface
  • 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「、」）...
  • 表 : Ⅰ名詞1 （外面;外表） outside; surface; external 2 （中表親戚） the relationship between the child...
  • 面 : Ⅰ名詞1 （頭的前部; 臉） face 2 （物體的表面） surface; top 3 （外露的一層或正面） outside; the ri...
  • 駐點 : arrest point
  • 表面 : surface; superficies; boundary; face; rind; sheet; skin; outside; appearance
  1. Micro - jets impingement cooling heat sink is used to cool the high power lda owing to the very thin hydrodynamic and thermal boundary layers in the impingement region when a jet impinges on a surface. reasonable array of jets can develop the uniform of temperature distribution on target very much

    微射流陣列冷卻熱沉，是利用射流沖擊在駐點區能產生很薄的邊界層來提高換熱效率的，合理的布置射流孔，可以極大的提高被冷卻表面溫度分佈的均勻性。
  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
  3. The solution formula of dwell time is deduced by using the pulse iteration method and the smoothing fourier transition method, and the formula can be simplified referring to workpiece shape. according to the anastomotic status of the tool and workpiece surface, we present the new model of the inherent relation among local pressure density, removal rate, convergence ratio and residual errors, and the corresponding formulas are given. the forming cause of the edge effect in the polishing process is analyzed, and the means which reduces the edge effect is put forward

    2 、針對計算機控制光學表面成形（ ccos ）的加工方式、誤差收斂特點，研製了去除函數呈高斯分佈的雙轉子結構研拋模；採用脈沖迭代法、平滑因子傅立葉變換法推導出駐留時間的演算法，求解過程中根據工件面形的特點作了各種形式的簡化；提出了工件表面和研拋模的吻合誤差與局部壓強、材料去除率、收斂比之間內在關系的數學模型，並推導出相應的計算公式；分析了邊緣效應產生的原因，在加工過程中採用相對壓力因子對去除函數進行修正，可以消除邊緣效應的影響。
  4. The method of prediction the discharge coefficients of film cooling holes on the turbine blade suggested by d. a. rowbury et. al has been improved in this paper to fit the computations in the cases of low pressure ratios and the holes in leading edge region especially. the effects of external cross - flow, hole geometry and reynolds number in the hole were taken into account. an additive loss coefficient method is subsequently applied to the test data in order to assess the effect of the external cross - flow

    Rowbury等提出的流量系數工程演算法進行了改進，計算結果和實驗數據的比較表明改進后的新模型使低吹風比和前緣駐點附近流量系數的計算得到了明顯的改進，而在高吹風比下仍能保持與實驗數據相符，這種演算法有可能成為低壓比情況下型面氣膜冷卻的一種通用設計方法。
  5. 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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