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題名 | Surface Pressure and Dynamic Characteristics on a Pitching Airfoil=等速上仰機翼之表面壓力與動力特性 |
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作者 | 陳志敏; 李俊輝; | 書刊名 | 中國機械工程學刊 |
卷期 | 18:6 1997.12[民86.12] |
頁次 | 頁567-578 |
分類號 | 447.63 |
關鍵詞 | 等速上仰機翼; 表面壓力; 動力特性; Dynamic stall vortex; Pressure measurement; Pitching airfoil; |
語文 | 英文(English) |
英文摘要 | 本文利用表面壓力量測探討等速上仰機翼之氣動力與動態失速渦流的特性。實驗 模型為NACA 0012機翼,以1/4弦為中心作0至30度的等速運動,其無因次上仰速率範圍在 0.0125至0.1之間,基於弦長的雷諾數為5.0X10�捰�2.0X10�瓣孜﹛C實驗結果顯示,隨著上 仰速率的增加,動態失速渦流在翼面的移動由等速轉變為慢快慢的非線性速度,其渦流強度 亦隨之增強。增加雷諾數對動態失速渦流移動速度的影響並不明顯,但似乎會減弱動態失速 渦流的強度。實驗結果亦顯示,升力失速與力矩失速的時差與上仰速率成正比而與雷諾數無 關。 w tempo at higher pitch rates, while it convects at a nearly constant velocity at a low pitch rate. The increasing of the Reynolds number has no significant effects on the convection velocity normalized. The pressure contours suggest that the DSV is strengthened by increasing the pitch rate and seems to be weakened by increasing the Reynolds number in the postvortex-convection stage. The time delay between the quarterchord moment stall and the lift stall is found to be proportional to pitch rate but independent of Reynolds number. |
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