Aerodynamic Performance Study of Blended-Wing-Aircraft under Severe Weather Conditions

淡江大學機構典藏 > 工學院 > 航空太空工程學系暨研究所 > 會議論文 > Item 987654321/84792

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题名:	Aerodynamic Performance Study of Blended-Wing-Aircraft under Severe Weather Conditions
其它题名:	翼胴合一飛機在惡劣天氣中之空氣動力特性研究
作者:	Wan, Tung;宛同;Song, Bo-Chang;宋柏璋
贡献者:	淡江大學航空太空工程學系
关键词:	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
日期:	2010
上传时间:	2013-03-22 19:38:46 (UTC+8)
出版者:	臺北縣淡水鎮 : 淡江大學航空太空工程學系
摘要:	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和環境的污染。近年來極端惡劣天氣變得相當頻繁，對於飛機起飛降落會造成相當大的影響。本研究主要運用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 確保本模擬是有可信度的。側風主要會影響飛機橫向和航向穩定性，如果穩定飛機經過本身調整會回到原有位置，如果不穩定，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響。希望研究成果對未來飛機設計及飛行安全考量都更有助益。 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.
關聯:	第七屆海峽兩岸航空太空學術研討會論文集, pp.69-79
显示于类别:	[航空太空工程學系暨研究所] 會議論文

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