本研究主要利用實驗探討翼前緣突節對變速型水平軸式風力機葉片性能之失速特性影響。葉片模型使用SD8000翼型為基礎並定義不同參數之突節振幅與波長進行比較。依照不同測試條件將實驗模型區分為全翼展及葉片轉件並透過風洞實驗來量測全翼展模型之升阻力曲線及葉片轉件功率、扭矩之性能曲線進而分析不同振幅與波長之翼前緣突節和葉片轉件的相互關係。從實驗結果發現，翼前緣突節較無突節模型能改善葉片高攻角失速之特性。其結果對於變速型風機因葉片開始轉動時失速所造成之能量損耗也有所改善。翼前緣突節之振幅參數影響較劇，受到葉片實度(solidity)影響，大振幅突節之特性曲線趨於平緩，對於失速區的效能提升較不顯著。在此研究中，在失速區段之性能表現由小振幅之翼前緣突節為佳。

In this study, the research is focused on the wind tunnel experiment of leading edge protuberances on blades performance at the stall region of small-scale horizontal axis wind turbine (HAWT) with variable rotational speed.The airfoil of all test model based on the SD8000 profiles with smooth (baseline) leading edge for comparison with the distinct definition of amplitude and wavelength of sinusoidal leading edge. The experiment was performed on the full-span models to get the coefficient of lift-drag ratio. Along with the full-span models, rotor blade models were also tested separately and the data for blade performance were evaluated.For all of the test model, the results indicated that the improvement of the stall effect of leading edge protuberances is significant with smaller amplitude for comparison with the baseline model. The curve of sin3 (A004,W0145) has higher C_p than other rotor models at the lower tip speed ratio between TSR= 3 ~4. Due to the effect of solidity, the larger amplitude produced a broad and flat curve means that the C_p is lower than others.

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