- 后緣渦流
- 尾渦
- trail: vt. 1.拖曳(衣腳等)，拖著走；拖帶著；提(槍)。 ...
- vortex: n. (pl. vortexes,-ti-ces ) 1 ...
- trailing edge vortex: 后緣旋渦; 隨邊旋渦
- trailing tip vortex: 尾梢渦
- trailing vortex cavitation: 尾渦空化
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trailing vortex中文什么意思
- 后緣渦流
- 尾渦
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例句與用法
- Trailing vortex cavitation
尾渦空化 - 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(qū)尾渦收縮和葉梢分離的非線型現(xiàn)象的影響；對于面元法，本論文采用的是計算較為簡便的基于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，并用morino導(dǎo)出的解析公式計算面元的影響系數(shù)的快速有效的數(shù)值預(yù)報方法。 - 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，分析并揭示了轉(zhuǎn)子葉道內(nèi)的馬蹄渦、通道渦、角渦、尾渦等復(fù)雜渦系及其與激波的相互干涉；特別是，分析并揭示了轉(zhuǎn)子葉道內(nèi)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(tài)及泄漏流動的發(fā)展，并著重給出了其與激波的干涉形態(tài)。 - 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
采用面元法預(yù)報大側(cè)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布.對于大側(cè)斜螺旋槳而言，槳葉表面采用常規(guī)的等半徑網(wǎng)格劃分方法在近葉梢處將導(dǎo)致大展弦比、大側(cè)斜和扭曲面元，這容易使槳葉表面速度的計算結(jié)果不正確，甚至?xí)?dǎo)致迭代過程發(fā)散及計算失敗.文中建立了一種“非常規(guī)網(wǎng)格”劃分方法，能有效地解決大側(cè)斜螺旋槳的計算和收斂問題.槳葉隨邊處通過迭代實現(xiàn)非線性等壓庫塔條件