Obtain the quasi steady lift coefficient, Eq. 8.51, and the boundary layer edge velocity, Eq. 8.52 for a chordwise flexible and parabolically cambered thin airfoil whose equation is given by Eq. 8.46, where the maximum camber location \(\mathrm{p}\) along the chord changes by SHM.

Eq. 8.51

Eq. 8.52

Eq. 8.46

Transcribed Image Text:

u' U 1-x 1+x =2a. (1+x) = 2a1-x