本研究係利用回應表面法在考慮、非穩態空氣動力與尾流動力環境下，尋求滿足直昇機於多重飛行狀態下的升力要求之最小總輸出功率的旋翼葉片。本研究結合了旋翼的空氣動力及尾流動力之緝令系統，並選用Peters
的尾流動力理論作為非穩態空氣動力環境模擬。回應表面法是一種建立近似系統整體反應的方法，利用在設計空間中不同觀察點建構出系統反應函數。利用該近似函數，可避免複雜繁瑣的靈敏度分析，進而快速地運用最
佳化方法求得最佳解。本研究採用縮小設計空間、增加實驗觀察點的數目等技巧於回應表面法中以獲得準確之反應函數，進而求出旋翼葉片弦長與扭角的最佳設計值。 This study presents an application of Response Surface Methodology (RSM) for a helicopter rotor blade design through an unsteady wake dynamic and aerodynamic coupling system. The unsteady wake dynamic system is simulated by the Peters finite state inflow theory. Response Surface Methodology is a method for global approximations to system behavior based on results calculated at various points in the design space. The technique of reducing the design space and increasing experimental data were used to achieve the accurately approximate function efficiently. The chord length and twist angle of rotor blade will be used as design variables to obtain the optimal configuration which to minimize the total power output and also maintain thrust in multiple flight condition.
