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    Please use this identifier to cite or link to this item: http://tkuir.lib.tku.edu.tw:8080/dspace/handle/987654321/84792

    Title: Aerodynamic Performance Study of Blended-Wing-Aircraft under Severe Weather Conditions
    Other Titles: 翼胴合一飛機在惡劣天氣中之空氣動力特性研究
    Authors: Wan, Tung;宛同;Song, Bo-Chang;宋柏璋
    Contributors: 淡江大學航空太空工程學系
    Keywords: 翼胴合一飛機;側風;大雨;二相流;空氣動力學;Blended-Wing-Body;Crosswind;Heavy rain;Two phase flow;Aerodynamics
    Date: 2010
    Issue Date: 2013-03-22 19:38:46 (UTC+8)
    Publisher: 臺北縣淡水鎮 : 淡江大學航空太空工程學系
    Abstract: 飛機設計的好壞來自於安全和效率,由於資源的損耗和短缺,傳統飛機已不符合和現代的需求。隨著
    科技進步,一種革命性的發展"翼桐合一飛機" ,擁有較好的升阻比和噪音值,能夠減少對燃油的消耗
    主要運用Pro/E 建立翼胴合一飛機外形,本文主要考慮的天氣因素是側風和大雨,並運用Fluent 模擬
    惡劣天氣的影響。在模擬側風和大雨對翼胴合一飛機的影響之前,須先驗證M6-wmg 確保本模擬是有
    果不穩定,則會造成偏轉、翻滾,對飛機造成重大響。本文假設lOrnls 、20m/s 和30m/s 的側風速度。
    大雨主要會影響飛機的升力和阻力,本研究運用DPM 機制模擬兩種大雨強度對翼胴合一飛機的影
    The goal of aircraft design is to achieve safe and efficient flight. In the world of civilian air transport,
    efficient, economically attractive configurations are urgently needed. Studies have shown remarkable
    performance improvements for the Blended-Wing-Body (BWB) over conventional subsonic transport. Also,
    if aircraft taking-off and landing will unavoidably face the strong crosswind orland heavy rain, and designer
    must put these severe weather influences into considerations. In this study, Fluent is used as simulation tool,
    the structure grid is generated by Gambit, and the standard M6 wing is first validated to ensure our
    simulation process is correct. The speed of crosswinds considered is 10rn/s, 20m/s and 30m/s. The resulting
    BWB's stability derivative values under crosswind are always smaller than Boeing 747-100, representing the
    intrinsic nature of BWB static unstable tendency. Also, the heavy rain influence of different rain rates is that
    the lift coefficient is decreased and drag coefficient is increased at all angle of attack spectrums, and liquid
    water content of 39g/m3 is more influential than 25g/m3, with maximum reduction of lift is at 0 degree and
    maximum increase of drag is at 6 degree AOA. The information gained here will be helpful for future
    transport aircraft designers and enhance flight safety.
    Relation: 第七屆海峽兩岸航空太空學術研討會論文集, pp.69-79
    Appears in Collections:[航空太空工程學系暨研究所] 會議論文

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