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].