淡江大學機構典藏:Item 987654321/38367
English  |  正體中文  |  简体中文  |  Items with full text/Total items : 62805/95882 (66%)
Visitors : 3953895      Online Users : 612
RC Version 7.0 © Powered By DSPACE, MIT. Enhanced by NTU Library & TKU Library IR team.
Scope Tips:
  • please add "double quotation mark" for query phrases to get precise results
  • please goto advance search for comprehansive author search
    •  Adv. Search
    Home ‧ Login ‧ Upload ‧ Help ‧ About ‧ Administer Goto mobile version


    Please use this identifier to cite or link to this item: https://tkuir.lib.tku.edu.tw/dspace/handle/987654321/38367


    Title: 超音速流經拋物線型翼剖面精確解之探討
    Other Titles: An Exact Solution of Supersonic Flow Past a Parabolic-Shaped Airfoil
    Authors: 馮朝剛;林志文
    Contributors: 淡江大學航空太空工程學系
    Keywords: 超音速線性化理論;超音速遠場非線性理論;Burgers方程式;曲線震波;supersonic linearized theory;Supersonic far fie1d;nonlinear theory;Burgers equation;Curved shock
    Date: 2006-03
    Issue Date: 2010-01-11 15:09:50 (UTC+8)
    Publisher: 臺北縣淡水鎮：淡江大學
    Abstract: Supersonic flow past a parabol ie-shaped airfoil constitutes a second-order boundary value problem. The supersonic linearized theory is only val id for calculating the flow wi thout any shocks in the near field. The exact solution in the physical domain of the boundary value problem can be obtained using the supersonic far field nonlinear theory. The solution captures successfully the leading and trai ling curved shocks. It can also be shown that the supersonic far field includes its linear solution in the near field.
    Relation: 第五屆海峽兩岸航空太空學術研討會論文集，頁23-30
    Appears in Collections:[Graduate Institute & Department of Aerospace Engineering] Proceeding

    Files in This Item:

    File SizeFormat
    index.html0KbHTML194View/Open

    All items in 機構典藏 are protected by copyright, with all rights reserved.

    DSpace Software Copyright © 2002-2004  MIT &  Hewlett-Packard  /   Enhanced by   NTU Library & TKU Library IR teams. Copyright ©   - Feedback