雷諾數范圍 的英文怎麼說

中文拼音 [léinuòshǔfànwéi]
雷諾數范圍 英文
reynolds number range
  • 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
  • 范 : 名詞1 [書面語] （模子） pattern; mould; matrix 2 （模範; 榜樣） model; example 3 （范圍） boundar...
  • 圍 : Ⅰ動詞1 （四周攔擋起來 使裡外不通; 環繞） enclose; surround; corral 2 （繞; 裹） wrap Ⅱ名詞1 （四...
  • 雷諾 : jean renoir
  • 范圍 : scope; limits; extent; boundary; confines; range; range dimension; spectrum
  1. 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。
  2. 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。
  3. In case of high reynolds number, the turbulence intensity of centreline drifted off its stable course in the sections, where the flow was in the transition

    在大雷諾數情況下，在流動處于發展階段的管長范圍內，流動中心處的相對湍流強度在入口擋環作用下偏離了穩定狀態。
  4. In accordance with different tripping annulus at the inlet, the numerical simulations of the reattachment length were performed with the " variable c ? " model. in the range of experimental reynolds number, the tripping effect on the reattachment length was developed in the figure. the dependence of the reattachment length on reynolds number was also analysed in the different status of pipe flow

    利用變模型常數的-模型針對不同尺寸的擋環進行了再附著長度的模擬計算，在實驗雷諾數范圍內，建立了入口處擋環對再附著長度影響的變化曲線，分析了再附著長度在不同的管流流動狀態下相對于雷諾數的變化情況。
  5. For both newtonian flow and non - newtonian flow, the vortices are generated when the waviness of the bottom profile is beyond a critical number. by increasing the waviness, a second vortex can be generated. with the increasing of reynolds number, the symmetry of the streamlines at re = 0 is destroyed and the vortices are sloped and become larger

    當波形板的波動度超出臨界值，波形板壁面上的流動出現流線分離，流動中有渦生成;增大波動度，流動中出現第二個渦; re = 0 ，流線在流場中對稱分佈;雷諾數增大，流線駐點在水平方向出現位置偏移，渦的范圍增大;對于非牛頓流體，隨著剪切變稀指數的減小，渦的作用范圍減小。
  6. The experimental model is a rectangular section of 15. 2 187mm ~ 2, which is composed of two aluminum plates. the angles between the internal netted rib turbulators and the flow direction are 45 ? for the one plate and 60 ? for the other, or both 45 ? for two plates. in the experiment, the re numbers changes from 0. 4 10 ~ 4 1. 5 10 ~ 5, rib width - to - pitch are 0. 25, 0. 3 and 0. 5, rib width - to - height are 0. 25, 0. 3 and 0. 5, the rib height - to - hydraulic diameter ratio is 0. 246

    主要研究了在通道進口截面積（即無肋處的截面積） a為15 . 2 187mm ~ 2 、肋高與通道當量直徑之比e / de等於0 . 246 ，實驗雷諾數范圍在0 . 4 10 ~ 4 1 . 5 10 ~ 5之間的情況下，雷諾數re 、肋向角a 、肋寬與肋高之比t / e和肋寬與肋間距之比t / p等參數對通道強化傳熱與流動阻力特性的影響。
  7. In this paper i was in virtue of the fluent software, set up the geometrical model of jin ’ ao mansion and adjacent buildings, used non - equilibrium wall functions to deal with the problem which come from the near wall, used realizable k - turbulent model to simulate the steady flow around 3d high - rise buildings, we can get the distribution of mean wind pressure coefficient of the surface of jin ’ ao mansion and five aerodynamics components. they were compared with the data from the wind tunnel test, we found out the distance between the result of the wind tunnel test and numerical simulation in the acceptable range

    本文以fluent軟體為平臺，建立金奧大廈及其周邊建築的計算幾何模型，近壁區採用非平衡壁面函數法處理，運用基於雷諾時均的realizablek -湍流模型進行高層建築三維定常風場數值模擬，獲得金奧大廈表面時均風壓系數分佈及基底五分量氣動力，並和風洞測壓試驗的結果及風壓系數積分計算的基底五分量氣動力相比較，發現兩者之間的差異在可接受的范圍之內。
  8. To prove the accuracy of the mach number, and the parameter homogeneity of the design nozzle " s exit, cfd calculate has carried on the design results. under the condition of supersonic and hypersonic flow, and a certain range of temperature, and mach number, the conclusion of the influence of specific heat to nozzle design is drawn

    為了驗證所設計的噴管出口馬赫數的大小和噴管出口流場的均勻性，採用nnd格式和b l湍流模型求解雷諾平均n - s方程，對設計結果進行了cfd驗算，得出了在一定溫度范圍內，超音速、高超聲速流動的條件下，不同馬赫數范圍內變比熱容對噴管型面和噴管出口馬赫數的影響。
  9. In this paper, the working fluid is air. experimental study of the nine different structure parameters of 3 - d ift with staggered arrangement fins in the reynolds number range of 250 to 30000 is performed to investigate the characteristics of heat transfer and flow friction behavior. analyses and reduces the experimental data by the least square method, obtains the nusselt and fanning friction fitting criterion equations

    本文以空氣為工質，在re 250 30000范圍內對九根具有不同肋形結構尺寸的肋叉排三維內肋管的換熱及流動特性進行了研究，並運用最小二乘法分析和處理實驗數據，獲得努謝爾特數，范寧摩擦系數與雷諾數，肋幾何參數的準則方程式。
  10. In a reynolds number range of 150 < 6500, a particle image velocimetry ( piv ) is used to measure and visualize the 2d flow over a backward facing step

    摘要利用粒子圖像測速技術（ piv ） ，對雷諾數150 < 6500范圍二維後向臺階的流動進行詳細觀測。
  11. A new coefficient of prandtl ' s relation was obtained from the experimental data. compared with three conventional relations of friction factor, the range of reynolds number was extended

    在實驗結果的基礎上提出了普朗特摩擦系數關系式的新系數，與常用的摩擦系數關系式相比，擴大了普朗特摩擦系數關系式的雷諾數應用范圍。
  12. The influence of difference in temperature, reynolds number of film, vacuum degree and spring parameter to the heat transfer capability on the evaporation side was studied through the uniform wall temperature experiment, by the result, the heat transfer coefficient on the evaporation side can be improved by inserting spring with proper parameter. when the reynolds number was between 4000 and 14000, and the heat transfer coefficient can be improved nearly 30 percents by inserting the fifth spring when the reynolds number nearly was 12000

    採用8種參數的螺旋線，通過恆壁溫實驗探討了傳熱溫差、雷諾數、真空度和螺旋線參數對蒸發側傳熱性能的影響，結果表明，插入參數合適的螺旋線，在雷諾數為4000 14000范圍內可以提高蒸發側傳熱系數，在雷諾數為12000左右時，加入5號螺旋線可以使蒸發側傳熱性能提高30左右。
  13. 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。
  14. So people are interested in the using of twisted - tape insert. a large number of researches on twisted - tape have been reported in the literature. but most of the researches were conducted with turbulent flows or laminar flows

    迄今為止，關于扭帶強化傳熱的研究已經取得不少成果，但這些成果或是在較高的雷諾數范圍或是在較低的雷諾數范圍獲得的，應用條件有明顯的局限性。
  15. The resolute of numerical calculation indicates that, when re > 100, the karman vortex - street appeares, the pressure on the surface of the circle cylinder is pulsing ; when re < 1, back - flow is appeared ; when re = 10, the coefficient of lift is comparable with the theory in 0 < 9. 25

    文中給出了雷諾數等於10時的升力系數計算結果並與理論值進行了對比，在一定范圍內與理論值有可比性。
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