where CL and CD are the coefficients of lift and drag, respectively. The density of air is given by ρ , wind speed V0 and length of airfoilc . For the purpose of simplicity an average angle of attack was assumed at 30° and the corresponding values of CLand CD were taken as 0.97 and 0.63 for the calculations [30].
The total thrust acting on an infinitesimal section of rotor blade is given by Eq. (5). Similarly, the moment produced by the incoming wind on an infinitesimal section of the rotor blade is given by Eq. (6). The total thrust and moment due to the wind were therefore computed by integrating Eq. (5) and Eq. (6) over the entire rotor blade. Details of the derivation of the BEM equations can be found elsewhere [30].