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    Please use this identifier to cite or link to this item: https://tkuir.lib.tku.edu.tw/dspace/handle/987654321/38371

    Title: 超音速凹角流動邊界值問題之相似精確解及其二階漸近解
    Other Titles: Similarity and asymptotic solutions of supersonic centered compression flow
    Authors: 馮朝剛;Feng, C. K.;侯昌桓;Hou, C. W.
    Contributors: 淡江大學航空太空工程學系
    Keywords: 超音速尖角流動;相似法;漸近展開;斜震波;Supersonic Corner Flow;Similarity Method;Asymptotic Expansion;Oblique Shock
    Date: 1997-12
    Issue Date: 2010-01-11 15:10:05 (UTC+8)
    Publisher: 臺南市 : 成功大學
    Abstract: 本文主要採勢流理論並利用相似轉換法, 求出超音速凹角壓縮流動完整邊界值問題之相似精確解及凹角表面完整之壓力係數, 並利用陡變條件求出斜震波。本文再利用漸近展開法, 直接由凹角壓縮流動之相似精確解展開, 而得出其擾動勢函數, 凹角表面壓力係數及斜震波位置之一階及二階漸近解, 並與斜震波理論之結果作一比較, 而驗證出本文理論及其結果之正確性。
    From the oblique shock wave theory, the exact shock relations and its asymptotic solutions for a wedge are discussed. In this paper, a systematic and rigorous approach for obtaining the exact similarity solution from the boundary value problem of full potential gasdynamic equation for supersonic flow past a wedge is exhibited. The unique solution in the compression region is obtained from the jump condition of the conservation form of the irrotationality. The asymptotic solutions to the second- order are obtained directly from the exact similarity solution and they agree well with the oblique shock wave theory.
    Relation: 中國航空太空學會八十六年年會暨第三十九屆學術研討會論文集=Proceedings of the 39th Conference on Aeronautics and Astronautics, R.O.C.,頁507-514
    Appears in Collections:[Graduate Institute & Department of Aerospace Engineering] Proceeding

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    超音速凹角流動邊界值問題之相似精確解及其二階漸近解 _英文摘要.docx摘要15KbMicrosoft Word103View/Open

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