尾旋葉 的英文怎麼說

中文拼音 [wěixuányè]
尾旋葉 英文
tail fenestron
  • 旋 : 旋Ⅰ動詞1 （旋轉） whirl 2 （用車床切削或用刀子轉著圈地削） turn sth on a lathe; lathe; pare Ⅱ名詞...
  1. 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。
  2. 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。
  3. Under the condition of knowing the mass, stiffness, damping and the real vibration response of stem, the propeller pressure impulses of blade frequency are deduced, these belong to structure dynamics problem that is loading identification problem

    摘要在已知船舶的質量、剛度、阻尼以及實測尾端振動速度的條件下，反推出螺旋槳葉頻激振力。
  4. When the propeller operates in the spatially non - uniform velocity field behind the ship, the unsteady cavitation on the blades often causes the vibration of ship structure, the propeller noise and the cavitation erosion on the blade

    在船尾非均勻流場中工作的螺旋槳，常常由於槳葉上產生了非定常空泡，導致船尾振動和螺旋槳噪聲，致使槳葉表面出現空泡剝蝕。
  5. The low - frequency discrete noise of the propeller is induced by the interaction between blades of the propeller and wake of the marine, and the low - frequency broadband noise of the propeller is produced by the interaction of blades and turbulent field of the marine stern

    螺旋槳的低頻離散譜噪聲是由船尾伴流場和葉片的相互作用引起的，而低頻寬帶噪聲是由船尾粘性湍流場和葉片的相互作用產生的。
  6. 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
  7. The computer program has following advantage : the solution of main blade is by iterative scheme in time domain, the kutta condition is used by explicit equal pressure condition, the jacobian matrix which can reflect the influence on the difference between the upper and lower surface at trailing edge by dipole is calculated in each iterative procedure, in order to improve the convergence of iteration

    本文編制的螺旋槳非定常性能預報程序是針對主葉在時域中迭代求解的， kutta條件採用的是顯式的等壓條件，求解中為了提高迭代的收斂性，在每次迭代中都重新計算反映偶極子強度對尾緣處上下表面壓力差影響的jacobi矩陣。
  8. The aerodynamic interference between the shroud and the propeller is calculated by lifting line theory. its precise, proved by wind tunnel test here, satisfies the engineering demand

    在計算螺旋槳的參數時，仍以有限葉數升力線模型進行處理，並用誘導因子法來計算槳葉尾渦系在升力線上產生的誘導速度。
  9. At the point of the second impact there was much debris from the tail fenestron and the antenna of the automatically deployable emergency locator transmitter ( adelt ) installed at the tail of the helicopter, suggesting a touchdown in a nose high attitude

    在第二次撞擊地點則發現許多尾旋葉及安裝于機尾的自動緊急定位發射器的碎片，顯示直升機著地時機頭朝上。
  10. Then a laplace equation can be deduced and through computation, the blade profile coordinates and geometry of the cascade result from an analytical solution. next, an optimization method, taking the geometry parameters of the unclosed profile as its objective functions, is used to obtain an optimized blade profile. and last, the optimized profile is refined with round arcs added in the leading and trailing edges

    本文採用的勢、流函數解析法法中，將無旋方程用新的類無旋方程替代，這樣在計算域上得出速度場的解析關系式，計算得出初始葉型；然後以此初始葉型的幾何參數，例如前尾緣的封閉程度和葉型彎角等為目標函數，通過優化程序對初始速度進行自動調節直到目標函數值最小為止。
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