微飛行器撓性薄膜翼及拍擊紊流器氣動力分析與測試

CHUR > College of Engineering > Department of Mechanical Engineering > Seminar papers > Item 987654321/35147

Please use this identifier to cite or link to this item: http://chur.chu.edu.tw/handle/987654321/35147

Title:	微飛行器撓性薄膜翼及拍擊紊流器氣動力分析與測試
Authors:	蔡博章 Tsai, Bor-Jang
Contributors:	機械工程學系 Mechanical Engineering
Keywords:	撓性薄膜機翼;拍擊翼;升阻比 Membrane wings;Flapping wings;Lift / drag ratio
Date:	2007
Issue Date:	2014-06-27 03:27:22 (UTC+8)
Abstract:	微飛行器發展主流:撓性薄膜翼與仿生物拍擊翼，撓性薄膜機翼可使高攻角可撓性薄膜翼CL續增而失速角可延後至30o~45o，但低雷諾數、低展弦比之層流脫離再依附之低壓區分佈，層流、過渡流及紊流模式尚未明確，邊際渦漩複雜流場對升阻比影響、低展弦比滾動不穩定較敏感及環境風速變動相較於飛行風速易產生Re與攻角連續變化等問題存在，本研究建構薄膜翼，啟動流體/結構數值模擬，原創仿生物拍擊機翼紊流器及水洞雷射測試，以強化空氣動力性能，提高升阻比與飛行穩定，改善邊際渦漩之複雜流場。流、固耦合低攻角數值模型已建立可分析撓性材料 The main streams of micro aerial vehicles development: membrane wings and insect-like / bird-like flapping wings. Membrane wings can keep continuously increasing CL as higher angle of attacks and delay the dynamic stall angle to . But laminar as flow in l
Appears in Collections:	[Department of Mechanical Engineering] Seminar papers

Files in This Item:

File	Description	Size	Format
微飛行器撓性薄膜翼及拍擊紊流器氣動力分析與測試.pdf		36Kb	Adobe PDF	50	View/Open