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    Please use this identifier to cite or link to this item: https://tkuir.lib.tku.edu.tw/dspace/handle/987654321/84783

    Title: 直昇機螺旋翼尾流場之數值計算
    Other Titles: The Numerical Wake Prediction of Hovering Rotors
    Authors: 陳慶祥
    Contributors: 淡江大學航空太空工程學系
    Keywords: 滯空螺旋翼;尾流;數值方法;阻力;升力;直昇機Hovering Rotor;Wake Flow;Numerical Method;Drag Force;Lift Force;Helicopter
    Date: 1995-12
    Issue Date: 2013-03-22 19:38:11 (UTC+8)
    Publisher: 臺北縣:淡江大學航空工程學系
    Abstract: 本文利用數值方法來計算直昇機滯空時螺旋翼的性能(升力,阻力)及其尾流形狀,此一數值方法結合一組軸對稱,不可壓縮Navier-Stokes方程式的計算和一個升力面的計算方法。升力面方法是用來計算螺旋槳葉片上的環流強度分布,此一環流分布輸入到Navier-Stokes的計算程式,算出此一環流分布下的尾流形狀,此一尾流形狀再輸入到升力面的程式,算出此一尾流形狀下的葉片環流分布,重複執行此一程序直到環流分布與尾流形狀都收斂為止。
    A numerical method based on the axisymmetric, incompressible Navier-Stokes equations is combined with a lifting surface method to predict the performance and vortex wake of hovering rotors. The lifting surface method is used to obtain the circulation distribution on the blade. This circulation distribution is served as input to the Navier- Stokes calculation to compute the shape of the vortex wake under this specified circulation distribution. The vortex wake is then input back to the lifting surface method to calculate the circulation distribution under this vortex wake. An iteration approach is utilized between these two methods to converge the circulation distribution and the shape of the vortex wake.
    Relation: 第一屆海峽兩岸航空太空學術研討會論文集,頁27-33
    Appears in Collections:[Graduate Institute & Department of Aerospace Engineering] Proceeding

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