尾渦面 的英文怎麼說

中文拼音 [wěiguōmiàn]
尾渦面 英文
trailing vortex sheet
  • 渦 : 渦名詞1. （漩渦） eddy; whirlpool; vortex 2. （酒窩） dimple
  • 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...
  1. Boeing wants to use existing wing and tail control surfaces that shift up and down about 20 degrees in a coordinated fashion to disrupt the vortical flow

    波音公司則利用現成的機翼與機尾控制面，讓它們互相協調、上下移動20度，以擾亂渦流。
  2. The vortex simulated in this article include the shedding vortex induced by the vane trailing edge boundary layer, the endwall vortex generated by the endwall boundary layer interaction, the passage vortex generated by the rotor rotation, and the leakage vortex generated by the tip clearance flow

    渦輪級內的渦運動包括：導向器葉片尾緣附而層引起的脫落渦；轉子通道內轉子的旋轉運動產生的通道渦；根腳區兩個端壁附面層干涉，形成的根腳渦；存在葉尖漏流時，出現的漏流渦。
  3. Based on an engineering background, through numerical simulation of the flow field in the hp turbine of the energy efficient engine ( e3 ), the article research the unsteady flow in a transonic turbine stage, the unsteady phenomena in the stage include the shockwave, wake, shedding vortex, endwall vortex, passage vortex and leakage vortex, etc. there are two shockwaves generated on the vane the tailing edge, one on suction side is named moving shockwave, and name another on pressure side steady shockwave

    本文首先對于研究的意義和國內外研究的現狀做了簡要的介紹，再從某工程背景出發，通過對e3發動機高壓渦輪內流場的數值模擬，研究了干涉的周期性的問題，以及渦輪級內常見的非定常現象：激波、尾跡、脫落渦、根腳渦、通道渦、漏流渦。導向器尾緣會出現兩道激波，在吸力面的激波可稱為「運動」激波，壓力面的激波可稱為「定常」激波。
  4. In this paper, some characteristics of flow movement and sediment transport are analyzed by using the flume experiment data. the cross section of compound channel can be divided into four regions : the undisturbed region in main channel, the interactive region between channel and plain, the undisturbed region in flood plain and the boundary region. in the undisturbed regions, the distribution of longitudinal velocity along the depth has the feature of lograithmic. whereas, in the interactive region, the longitudinal velocity does not obey the logarithmic distribution law, but it can expressed as a revised logarithmic function by using a wake function. on the basis of the kinematic equation the velocity distribution of transverse velocity is obtained. in the boundary region, the longitudinal velocity obeys the law of parabolic distribution. furthermore, according to the simplified diffusion equation, the transverse distribution of sediment concentration in the interactive region is deduced. the analysis is in good agreement with the measured data

    本文根據漫灘水流的運動特點，將漫灘水流的復式斷面分為主槽平衡區、灘槽交互區、灘地平衡區及邊壁區等4個區，並給出了各區寬度的經驗公式.根據灘槽交互區垂線流速分佈的變化特點，提出了附加尾流函數的對數流速分佈公式.在簡化水流運動方程和泥沙擴散方程的基礎上，對灘槽交互區內垂線平均流速及含沙量沿橫向分佈進行了理論分析，提出了反映灘槽水流動量交換強度的橫向渦量粘性系數及橫向擴散系數的表達式，得到了漫灘水流垂線平均流速及含沙量沿橫向分佈的解析解，並與實測資料吻合較好
  5. Based on the green ' s formula and the assumption of the propeller blade ' s thin sections, a lifting - surface method of propellers with the vortex lattice and equal source panel distributions on the mean camber surface has been introduced for the prediction of steady propeller ' s hydrodynamics in this paper. an approximate kurta condition was applied

    基於creen公式和薄翼理論假設導出的升力面方法，採用在螺旋槳拱弧面上分佈離散渦、源布置方法預報均勻流場中的螺旋槳的定常性能，螺旋槳尾渦面上壓力連續性條件採用近似的kutta條件處理。
  6. The results indicated that the generation of trailing - vortex of downstream adjacent vanes could be restrained effectively by upstream wake when the passing frequency and the amplitude of wake defect satisfy some conditions, associated with a significant enhancement of time - averaged aerodynamic performances : loss coefficient reducing 40. 2 % and the ratio of loading coefficient and loss coefficient increasing 93 %

    研究表明：滿足一定通過頻率和虧損幅值條件的尾跡能夠有效抑制下游相鄰葉排尾緣渦的生成，達到控制或是推遲附面層非定常分離的目的，從而使得流場時均性能大幅度的提高，損失系數降低了40 . 2 % ，功損比增加93 % 。
  7. The surface of propeller, hub and the vortex of blade is discreted by a number of small hyperboloidal quadrilateral panels with constant source and doublet distribution

    槳葉、槳轂表面和螺旋槳尾渦面採用四邊形雙曲面元離散，以消除面元間的間隙。
  8. Eventually mode a and b coexist in the wake, which confirms the previous studies. besides, the present paper finds that downstream the streamwise

    從圓柱表面到旋渦形成區、到近尾跡再到下游尾跡流向渦結構從模式a轉換到模式b 、雙渦對模式、再恢復為模式a 。
  9. Large eddy simulation of gas - particle two phase turbulence was carried out, such as simulation of two - dimensional gas - particle two phase wake, two - dimensional gas - particle two phase jet and three - dimensional gas - particle two phase rectangular jet. in these works, les was adopted to simulate gas phase flow and lagrangian approach was utilized to simulate the particles " motion. a series of significant and interesting results were obtained

    文中對二維氣粒兩相平面尾跡流場、二維氣粒兩相平面射流流場以及三維氣粒兩相矩形射流流場中的氣相流場進行了大渦模擬、對顆粒運動擴散採用lagrangian模擬研究后，取得了一系列具有重要的理論意義和實際意義的研究成果。
  10. Stay cables of the long - span cable - stayed bridges are susceptible to vibration under wind loading, or wind incorporated rain excitation, or deck motion due to high flexibility, relatively small mass and very low inherent damping, such as vortex shedding, wake galloping, parameter resonance and wind - rain induced vibration. large - amplitude vibration of cables may reduce the life of cables and threaten safe traffic, and has been considered today as one of the most critical problems for this type of bridge

    大跨度斜拉橋拉索具有較小的質量和極低的阻尼，在風、風雨及橋面振動等外部激勵下極易發生振動，如渦激共振、尾流馳振、參數共振和風雨振等，拉索的大幅振動對拉索的使用壽命和橋梁安全運營構成極大威脅，它已成為大跨度斜拉橋急需解決的關鍵問題之一。
  11. And then simulations of gas - particle two phase plane wake and gas - particle two phase plane jet were carried out by using this model. after numerical simulations of the two flow fields were finished, series of analytical work was done. first, the distribution of time - averaged velocity, turbulence intensity was analyzed, and some of the simulation results were compared with those of the experiments ; the coherent structure of vortices in the near wall region of the plane wake flow were studied by describing the evolution of the eddy structures, including the forming, developing and shedding from the wall of the vortices in the near wall region ; the coherent structure of vortices in the whole field was also studied, such as the forming, developing, moving, pairing and merging of the eddies etc.

    在對上述兩種流動形態的二維大渦模擬研究中，首先全面地分析了氣相時均流場的速度、湍流強度的分佈規律以及氣相速度的脈動規律等並就部分數值模擬結果與實驗結果進行了對比研究；分析了平面尾跡流場中近壁處旋渦擬序結構，全面和逼真地反映了近壁處旋渦的生成、發展和脫落的規律；描述分析了平面尾跡流和平面射流的全場流動旋渦擬序結構，從整個流場的角度反映旋渦的生成、發展、運動以及旋渦之間相互配對、合併的作用規律等。
  12. The complex vortex system structure and shock wave system structure inside this rotor is obtained. wall flow patterns on the blade surface and hub surface are found out. the complex vortex system structure, such as horseshoe vortex, passage vortex, corner vortex and trailing vortex, and the interaction with shock wave system are researched. especially, the character of the tip clearance flow inside the rotor passage is revealed, and the interaction between shock wave and tip clearance flow near blade tip and the evolution of tip clearance flow are considered

    給出了葉片表面及輪轂面上的壁面流型，分析並揭示了轉子葉道內的馬蹄渦、通道渦、角渦、尾渦等復雜渦系及其與激波的相互干涉；特別是，分析並揭示了轉子葉道內頂隙射流的特點，得到了頂隙附近激波與泄漏流動的干涉形態及泄漏流動的發展，並著重給出了其與激波的干涉形態。
  13. During past year, 28 times of measurements for two units of b plant of zhelin hydropower station were made, the states of pressure pulsation in the draft cone tube, head cover and spiral case of units were acquired under different water heads, and the influences of that on safety and stability of units operations were also acquired

    摘要在長達一年多的時間里，對柘林水電廠b廠兩臺機組進行了28臺次試驗，全面掌握了機組各水頭下尾水錐管、頂蓋和渦殼中的壓力脈動情況，以及對機組安全穩定運行的影響。
  14. The surface panel method has been applied to predict the hydrodynamic performance of highly skewed propeller. the surface of propeller and its trailing vortex are discreted by a number of small hyperboloidal quadrilateral panels with constant source and doublet distribution. for highly skewed propeller, the conventional method generating grid oriented along constant radii will result in a high aspect ratio and a high skewness and a twist panel near the propeller tip on blade surface, which result easily in incorrect calculation results of velovity on blade surface, even in iteration divergence and calculation failure. a “ non - conventional grid ” is developed to acoid these problems. this grid can effectively solve the problem of the calculation and convergence for highly skewed propeller. the non - linear kutta condition of equal pressure on upper and lower at the trailing edge is executed by the iterative procedure. by sample calculating, the obtained results are satisfied the experimental data

    採用面元法預報大側斜螺旋槳水動力性能，螺旋槳表面及尾渦面離散為四邊形雙曲面元，每個面元上布置等強度源匯和偶極子分佈.對于大側斜螺旋槳而言，槳葉表面採用常規的等半徑網格劃分方法在近葉梢處將導致大展弦比、大側斜和扭曲面元，這容易使槳葉表面速度的計算結果不正確，甚至會導致迭代過程發散及計算失敗.文中建立了一種「非常規網格」劃分方法，能有效地解決大側斜螺旋槳的計算和收斂問題.槳葉隨邊處通過迭代實現非線性等壓庫塔條件
  15. In lifting - surface theory, the non - liner phenomena of the trailing vortex in the transition wake area and of the tip vortex separation are considered. in surface panel method hyperboloidal quadrilateral panels are employed and the morino ' s analytical formulation is used to determine the influence coefficients. the more reasonable pressure kutta condition is satisfied at the trailing edge of propeller blade

    在計算中，對于升力面理論，本論文考慮了過渡區尾渦收縮和葉梢分離的非線型現象的影響；對于面元法，本論文採用的是計算較為簡便的基於擾動速度勢的基本公式及雙曲面形狀的面元，在槳葉隨邊滿足更趨合理的壓力kutta條件，並用morino導出的解析公式計算面元的影響系數的快速有效的數值預報方法。
  16. At first, the generating mechanisms of four kinds of wake features are studied in the thesis. we have simulated the features of ocean surface waves, kelvin wake, narrow v wake, turbulent wake, vortex wake, and internal wake. the kinetic equation of kelvin wake have been analyzed and improved, which can be used to calculate the kelvin wake of a submerged moving body

    論文首先研究了四種常見尾跡特徵的產生機理，模擬得到了海面、 kelvin尾跡、窄v尾跡、湍流和渦流尾跡以及內波尾跡特徵；改進了kelvin尾跡的動力學模型，使之能夠計算運動物體下潛后的kelvin尾跡波高分佈。
  17. To meet the needs for wider surge margin of the turbofan engine, a new model was developed to predict the characteristics of the fan / high pressure compressor and turbine in this thesis. several ways, including, variable inlet guide vanes of the fan, variable guide vanes of the high pressure compressor, the variable inlet area ratio of the mixer and the nozzle areas, were presented to enlarge the surge margin of the turbofan engine. meanwhile, a method of combined variable geometries for optimizing controls of inlet guide vanes of the fan, guide vanes and the first two stators of high pressure compressor, area ratio of mixer and noz zle areas was established

    為了滿足下一代作戰飛機對推進系統的性能和穩定性要求，本文建立了壓縮系統特性和渦輪特性的新模型，並分別採用改變渦扇發動機風扇進口導流葉片、壓氣機導流葉片和前兩級靜葉片、混合室進口處內、外涵面積比和尾噴管面積，研究了其對發動機性能和穩定性的影響，進而得出了渦扇發動機變幾何擴穩的方法，為發動機變幾何擴穩研究打下理論基礎。
  18. The results are compared with the cases in a single - layer fluid, showing that the density stratification can have a relative large effect on the drag and lift coefficients as well as the vortex shedding

    計算受迫振蕩圓柱體的升力系數、阻力系數隨時間的演化曲線和圓柱體的尾渦分佈，以及圓柱體的受迫振蕩激發兩層流體內界面的擾動，並與均勻流體的情況進行了比較分析。
  19. Moreover, aircraft actually generate several vortices ? off the tail flaps, control surfaces and other areas of air - pressure discontinuity, states alan j

    此外，連續體動力學公司的總裁畢拉寧說，飛機其實會產生好幾個渦流- -尾襟翼、操縱面與其他產生氣壓不連續的區域。
  20. The duct and it ' s vortex is discreted by a number of small straight quadrilateral panel. constant source and doublet distribution is placed on each panel on the surface of body, and constant doublet distribution is placed on each panel on the surface of vortex

    以面元的幾何形心為控制點，在每個物面面元的控制點上布置等強度的源匯分佈和偶極子分佈，每個尾渦面面元控制點上布置等強度的偶極子分佈。
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