本研究主要利用數值模擬與風洞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並以田口方法設計實驗參數組合，以較精簡的次數找尋適合於變速型水平軸式風力機翼前緣突節葉片最佳幾何參數設計。從數值模擬及風洞實驗結果發現，其最佳化突節參數可用於葉片元素動量理論之葉片，改善葉片低轉數高攻角失速之特性並對於葉片扭矩值及效率有所提升。
利用數值模擬觀察葉片表面之流場現象，可發現具有翼前緣突節之葉片會在葉片低轉數失速時在波谷區有渦流匯聚效應，此一效應也為其葉片在失速時扭矩值的來源。這現象可證明翼前緣突節葉片可利用於流場控制特性來提升水平軸式風力機葉片性能之失速特性。

In this study, the research is focused on the numerical simulation and wind tunnel experiment of leading edge protuberances on blades performance at the stall region of small-scale horizontal axis wind turbine with variable rotational speed. Taguchi Method has been used to set up the numerical experiments in search of a set of geometric parameters of leading edge protuberances on blades.From numerical simulation and wind tunnel experimental results showed that the optimal parameters of the leading edge protuberances on blades has higher C_p and torque than other without the leading edge protuberances rotor models at the lower tip speed ratio.
From observing the flow fields on the blades, it can be seen that the sinusoidal leading edge begin the vortex convergence phenomenon. The vortex convergence phenomenon can improve the performance during the stall region for HAWT, and this result show out the flow control in the blade is possible.

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