槳葉曲度 的英文怎麼說
中文拼音 [jiǎngyèqūdù]
槳葉曲度
英文
curve of blade-
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Now, it is important to develop the composite blade researching, two measures including analysis methodology and finite methodology are provided. in this text, the finite rotation composite beam theory developed by hodges and his co - workers, during the late 1980 ' s, is adopted in order to research rotor of helicopter. a liner and two - dimension finite analytic measure is used to calculate the section characteristic and strain of the blade ; a semianalysis methodology is used to calculate the sensitive degree of section characteristic
以giavotto的線性二維有限元分析模型為基礎考慮了復合材料槳葉的結構和變形特點，計入了剖面翹曲的影響，在此基礎上編制了具有八節點等參元復合材料槳葉剖面剛度計算的有限元程序，分析計算了復合材料梁的剖面剛度、彎曲中心、剪切中心；並利用半解析法進行剖面剛度、剪切中心、彎曲中心的參數靈敏度分析。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。
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