雷諾數 的英文怎麼說

中文拼音 [léinuòshǔ]
雷諾數 英文
nr
  • 雷 : 1. （雲層放電時發出的響聲） thunder 2. （軍事上用的爆炸武器） mine 3. （姓氏） a surname
  • 諾 : Ⅰ動詞（答應; 允許） promise Ⅱ感嘆詞（答應的聲音） yesⅢ名詞（姓氏） a surname
  • 數 : 數副詞（屢次） frequently; repeatedly
  • 雷諾 : jean renoir
  1. Numerical analysis of low - reynolds - number flow over airfoil

    繞翼型低雷諾數流動的數值分析研究
  2. Then, the program is used to simulate the flow across the backward - step, and the conclusion is testified that the circumfluence length is related to the reyonlds number

    同時，利用程序對后臺階繞流流動進行計算，驗證了后臺階繞流迴流長度和雷諾數有關的結論。
  3. This turbulence caused the flow pattern in the tunnel to be similar to the flow pattern in free air at a higher reynolds number.

    這種紊流使風洞內的流譜與在較高的雷諾數下自由氣流中的流譜相似。
  4. The critical value of these parameters and that of flow pattern criterion reynolds number of newtonian fluid are equally possessed of the character irrelative to fluid rheological property

    這些參數的臨界值與牛頓液體流態準數雷諾數的臨界值，同樣具有與液體流變性無關的特點。
  5. If the reynolds number is large the flow is no longer laminar as the particles tend to move in a random manner.

    如果雷諾數很大，由於流體質點變成雜亂無章的運動流動不再是層流。
  6. ( 2 ) the results reveal that the pre - swirl ratio has a great influence on the flow field of the rotating disk, even greater than the rotational reynolds number, and an initial constant is induced in moment coefficient cm and average nusselt number nuave correlations, which does not exist in the case of without pre - swirl

    （ 2 ）分析了預旋系數_ r對該旋轉盤腔流場的影響，定義了一個新的壓力系數c _ p ，該壓力系數c _ p沿徑向位置的變化對特定的旋轉雷諾數re _是一個常數。
  7. The effect of reynolds number on rudder hydrodynamic performance is also analyzed. up to the stall angle the computed lift and drag agree well with measurements and other author ' s calculations, whereas stall angle, lift and drag beyond the stall angle are slightly under - predicted. the solver is used to investigate laminar and turbulent separated flows around a 6 : 1 prolate spheroid at high incidence angles and their effects on hydrodynamic forces

    應用所開發的求解器，以naca0015翼型舵為算例計算了船舵在不同雷諾武漢理三;大學博士學位論文數下大舵角范圍內的三維粘性流場及水動力，成功地預報了舵的失速角和最大升力，並初步探討了雷諾數對舵水動力的影響;計算結果與現有試驗和計算數據比較，吻合程度相當好，初步檢驗和驗證了該求解器精確模擬粘性流動和計算水動力的能力。
  8. Reynolds finds that turbulence begins when r exceeds about 2000.

    雷諾發現當雷諾數大於約2000時開始產生湍流。
  9. The results indicate that : the high positioned air inflow do good to heat transfer in rotator disk ; different size of radial outflow have small effects on flow and heat transfer ; the heat transfer near rotating disk increases as rotating reynold number increases or non - dimensional mass flow rate increases

    結果表明，高位軸向進氣對轉盤換熱有利；不同的徑向出口大小對盤腔內的流動換熱影響不大；隨旋轉雷諾數和無量綱質量流量增加，轉盤盤面的換熱效果增強。
  10. By comparing the results with relative experiment data, it is shown that rng k - is more exactly than the other turbulent model. 2 ) the influences of axial inflow position, radial outflow size, rotating reynold number, non - dimensional mass flowrate and axial inflow angle on the flow and heat transfer characteristics were numerically investigated for a typical rotator - stator cavity with axial inflow, radial inflow and radial outflow. the correlations for average nusselt number vs rotating reynold number or non - dimensional mass flowrate were established

    （ 2 ）針對一典型的徑向、軸向進氣，徑向出氣的轉-靜盤腔結構，系統研究軸向進氣位置、徑向出口大小、旋轉雷諾數、無量綱質量流量和軸向垂直預旋進氣等對盤腔內流動和換熱的影響，整理出轉-靜盤腔內轉盤平均努謝爾數與旋轉雷諾數無量綱質量流量之間的準則關聯式。
  11. 4 ) in a pre - swirl rotator - stator cavities with discrete pre - swirl nozzles and blade - cooling entry holes, the influences of pre - swirl angle and flow parameter on the flow and heat transfer characteristics were numerically investigated. the correlation for average nusselt number vs rotating reynold number or non - dimensional mass flowrate were established. the results show that : advantage of per - swirl inflow is the effect of cooling the blade - cooling entry holes ; pre - swirl inflow increases heat transfer in rotating disk of pre - swirl chamber ; as pre - swirl angle increases, local nusselt number decreases in pre - swirl chamber ; the temperature of stator of inner rotator - stator chamber and per - swirl chamber decreases as rotating reynold number increases ; when the axial mass flowrate maintains constant, heat transfer in the rotating disk of inner rotator - stator cavities does n ' t change as per - swirl mass flowrate increases, while heat transfer in the rotating disk of per - swirl chamber increases ; when the pre - swirl mass flowrate maintains constant, change of the axial mass flowrate has effect on the whole cavity

    結果表明，預旋進氣的優點在於增強了葉片冷卻孔附近的對流換熱效果，局部努謝爾數隨預旋角的增大而有所減小；隨旋轉雷諾數的增加，不論是內轉靜腔室還是預旋腔室的靜盤上的溫度都不同程度的降低：當軸向中心進氣質量流量不變時，隨預旋進氣的質量流量增加，內轉靜腔室的轉盤盤面上的換熱基本沒有變化，而預旋腔室的轉盤盤面上的換熱效果增強；當預旋進氣質量流量不變時，軸向中心進氣的質量流量的改變對整個盤腔都有影響。
  12. The linear scaling and the reynolds number represent classical, aerodynamic similitude requirements applicable to law-speed flight.

    線性縮尺和雷諾數是低速飛行時經典的氣動力模似要求。
  13. Effect of reynolds number on turbine cascade flow

    雷諾數對渦輪葉柵流動的影響
  14. Results show that the influence of mainstream reynolds numbers on heat transfer coefficience is little and the heat transfer coefficience raise with the increase of reynolds numbers. the influence of the position of holes on heat transfer coefficience is complex and correlate with the mainstream speed and the balde surface curvature. and the influence of blowing ratio on heat transfer coefficience is more great ( especially to stator ), and show a complex relation to mainstream reynolds number and the position of holes

    實驗結果表明，不同孔位出流的換熱由於孔排下游表面來流速度及葉片表面曲率的不同而有不同的規律，而主流雷諾數對葉片表面特別是壓力面和前緣區域的換熱系數比的影響較小，吹風比對換熱系數影響較大（特別是導葉） ，並且隨氣膜孔位置和來流雷諾數的變化而情況復雜。
  15. 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。
  16. Reynolds numbers ( based on average velocity at passage inlet and hydraulic diameter of the passage ) are changing from 20000 to 80000 and the extraction ratios ( suction ratios, sr ) are changing from 0. 30 to 0. 60 for each test model. so the influences of reynolds numbers, suction ratios and etc. on the discharge coefficients and pressure loss characterist ics are also presented. flow fields of typical passages are visualized with the flow visualization techniques and measured with hot - wire anemometer

    對每一種通道結構，實驗在不同通道進口雷諾數（ re = 20000 、 40000 、 60000 、 80000 ）和不同通道總出流比（ sr = 0 . 30 、 0 . 45 、 0 . 60 ）下進行，以研究這兩個流動參數及其它相應變化的參數（氣膜孔的雷諾數re _ h 、氣膜孔與通道的動量比i等）對出流特性和流阻特性的影響規律。
  17. The effects of reynolds number, back surface of nozzle, aft - dome configuration and degree of submergence on aft - end internal flow were studied by both cold gas simulation and numerical simulation. it is showed that the separated flow is sensitive to the change of reynolds number and aft - end cavity configuration

    最後，利用冷流模擬與數值模擬相結合的方法，研究了雷諾數、噴管背壁形狀、后封頭形狀和潛入深度對燃燒室尾部流場的影響，結果表明流動的分離對雷諾數和背壁區幾何邊界的變化很敏感。
  18. The results show that, comparing with the gas pressure drops calculated by the modified ergun equation, in the cases of the gas reynolds number is small, due to the presence of the dead space, the observed p in the experiments are bigger than that obtained by calculation, and when the gas reynolds number is large, because of the small interfacial viscous drag - force between gas and liquid, the p observed are smaller than that obtained by calculation

    結果表明在氣相雷諾數較小時，由於停滯孔隙率的存在，實測壓降值比修正厄根方程計算的值大；氣相雷諾數較大時，氣液界面上產生的粘性曳力較小，實測壓降值比修正厄根方程計算的值小。
  19. The blade inner channel cooling is a complex convection - conduction coupling problem. this thesis build a three - dimension. compressible turbulence model, and give a general solve method. with the geometrical model of the glossily rectangle straight channel, the rectangle straight channel with in - line arrays disturb plates, the rectangle straight channel with staggered arrays disturb plates, the rectangle straight channel with slant disturb plates, this thesis compute the flow and heat transfer condition when the cold air path though these channels, and gain the temperature field, pressure field, velocity filed, in addition. this thesis also analyze the influence of the different channel height, the different channel materials, the different channels, and gain the function relation between he nusselt number, friction factor and reynolds number. this thesis is emphasis on the new heat transfer enhancement structure, that is, disturb plates, with the comparison with the glossily channel and channel with pin fins, the heat transfer enhancement effect of the former is better, and the conclusion can be used in the design of aircraft blade

    葉片內部通道冷卻是一個復雜的對流?導熱耦合傳熱問題，本文在分析葉片內部通道冷卻的流動與傳熱情況的基礎上，建立了三維、可壓縮紊流的物理模型，得到了通用的求解辦法；利用不帶擾流片的矩形直通道、帶順排擾流片矩形直通道、帶叉排擾流片、帶傾斜擾流片的矩形直通道的幾何模型，計算了冷卻空氣通過這幾種通道時的流動與換熱情況，得到了各種不同情況下計算區域的溫度場、壓力場、速度場；在此基礎上分析了不同的通道高度、不同的葉片通道材質對葉片內部通道冷卻的影響，並整理得到了各種通道形式下，努謝爾數和阻力因子與雷諾數的函數關系；本文重點研究了新型的葉片內部通道冷卻強化傳熱措施?帶擾流片的內部冷卻通道的強化傳熱效果，通過與光滑矩形直通道、帶針肋通道的冷卻效果的比較，表明了這種新型鮚構的優勢，對于葉片內部通道冷卻結構的設計可以起到指導的作用。
  20. In this paper, by checking up the heat calculation about the experiment results of the single row tube and double waves belt, i come at the function of the heat transfer factor j and the reynolds number re, i also come at the function of the f r i ct i on factor ^ " and the reyno i ds number re

    本文還通過對單排雙波帶散熱器的實驗結果進行校核熱計算，回歸導出該種散熱器的傳熱因子j及摩擦因子f與雷諾數re的數學表達式，從而為用這種芯子根據廠家要求設計散熱器提供了理論依據。
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