查詢結果分析
相關文獻
頁籤選單縮合
題名 | The Investigation of Lift Force Performance for a Fixed Wing Micro Aero Vehicle= |
---|---|
作者 | Tsai, Bor-jang; Zheng, Zhe-chang; Ho, Wu-chi; |
期刊 | Journal of Aeronautics, Astronautics and Aviation. Series A |
出版日期 | 20060300 |
卷期 | 38:1 民95.03 |
頁次 | 頁11-19 |
分類號 | 447.553 |
語文 | eng |
關鍵詞 | Micro aerial vehicle; Aerodynamic; Flow field analysis; |
英文摘要 | The objective of this paper is to study the aerodynamic performance of a micro airplane with 16cmchord length, 20cm wingspan, aspect ratio 1.25, calculating the 3-D aerodynamic properties and simulating the flow-field of a micro airplane’s Clark Y-type wing. This was in order to understand the problems encountered in the low aspect ratio and low Reynolds-number conditions. During this study counter-circulation phenomena; flow will have separation and reattachment to form so called “bubble” phenomena would occur when the angle of attack reach ±10°. In the 3-D cases, the lift coefficient with a vertical tail’s slope will be slightly greater than that without a vertical rudder. The trend of the lift coefficient observed in the water-tunnel experiment matched that of the numerically calculated results. Also in the flow-field visualization, the dye will separate from the airfoil surface at two-thirds of the chord length and counter-circulation phenomena will occur. After the fixed wing design and aerodynamic analysis, a CAD/CAE/CAM module window platform is established as well. |
本系統之摘要資訊系依該期刊論文摘要之資訊為主。