An infinitely thin "flapped plate" is represented by two straight lines. The leading edge
is located at x=y=0, the hinge point is located at x=0.65c,y=0.05c and the trailing
edge is located at x=c,y=0. The plate is immersed in a flow with freestream velocity
U_(0)cos(\alpha ) in the x-direction and U_(0)sin(\alpha ) in the y-direction.
Use thin-aerofoil theory to derive an expression for the sectional lift coefficient.
Calculate the zero-lift angle of attack. Finally, plot the sectional lift coefficient against
angle of attack or angles between \alpha =-10\deg and 5\deg .