Abstract
Aerodynamic performance characteristics of the HAWT were investigated theoretically and experimentally by the combination analysis of momentum, energy, and blade element theory superimposed by the strip element theory, and by a small-scale model, considering the angular rotation of working flow, hi this study, four types of wing section and arrangement of blade were examined by a small scale experiments under the condition of open typed wind tunnels with free stream 0.8〜4.5 m/s and outlet ducts dia. of 0.88m φ. i.e., tapered rectangular blade with NACA44, LS04 and two-stage pitch angle tapered blade and tip oval tapered blade with NACA44. The aeronautical characteristics of the H. A. W. T. employing the different blades were discussed to the relation of C_P, C_T, C_q and tip speed ratio λ, based on the experimental and analytical results. Prediction results of aeronautical characteristics for large scale unit are cleared how to be optimized design parameters acting as significant role.
