抄録
Aerodynamic performance characteristies of the HAWT were investigated theoretically by the combination analysis of momentum, energy, and blade element theory by using the strip element theory, and experimentally by a sub-scale model, by considering the angular rotation of working flow. IN this study, no twist rectangular blade with NACA44 series aerofoil were examined by the analytical results under the condition of open typed wind tunnels with wind stream 0.8∿4.5m/s and outlet ducts dia of 0.88mΦ. The aeronautical characteristics of the H. A. W. T. were cleared to the relationship between C_P, C_T, C_q and tip speed ratio λ, and the far wake flow velocity distribution, for the pitch angle as parameter. Particularly, slotted flap was considered to avoid a stall of the blade for a gust with vortex, therefore, the rectangular blade with a single-slotted flap was examined by experiment. Obtained results were discussed under the same condition as parameter of attack angle and flap angle acting as significant role.
