jet geometry 中文意思是什麼
jet geometry
解釋
噴流幾何形狀-
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。 -
Then the thermal visualizations of jet impingement cooling with single or double row holes inside semi - enclosed ribbed channel are measured by using infrared camera and the effects of flow and geometry parameters on convective heat coefficients are obtained. the results show that : the impingement cooling effectiveness of ribbed surface is affected greatly by the jet - to - surface spacing, and the best effectiveness is achieved under the jet - to - surface spacing equals to 1. the correlation formulas of impingement heat transfer characteristics to the parameters are finally concluded and in good agree with the experiment data
最後，對單排、雙排沖擊孔試驗板在半封閉通道展開了流量系數的研究，在變化各種幾何因素及流動因素的情況下由實驗得出了沖擊孔流量系數值，討論並分析了各種因素對流量系數的影響程度，建立了沖擊孔流量系數的準則關系式，與實驗結果對比表明:該準則關系式與實驗實測數據吻合較好，精度較高，有較高的工程應用價值。 -
And then based on a surface - to - air missile that satisfies the requisition nearly, by means of reconstructing its geometry size, subsystems such as engine, the interceptor model used to continue the following studies is established. then the trajectory - control jet or attitude - control jet is added to the interceptor based on the analysis of the relationship between the missile performance and the thrust and configuration of the side jet
然後以基本滿足方案要求的某型防空導彈為基礎，對其幾何尺寸、發動機等分系統進行改進，並通過分析導彈性能與側噴發動機參數之間的關系，增加了姿控或軌控側向裝置，這樣得到了本文的研究工作所需的導彈模型。
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