Consider a thin, symmetrical aerofoil at 1.5 angle of incidence. From thin aerofoil theory, calculate the lift coefficient and moment coefficient about the leading edge. (Answer C = 0.164, CMle = -0.041) An aerofoil has the parabolic camberline given by: y y(x) = 4h (1 - 4) y(x) U h 2/c Where h is the maximum height (camber) and c is the chord. Using thin aerofoil theory, show that: C = (a = 2 + 12h) Use the general equations for thin aerofoil theory: U (ay dx kdx 1 - = 2 x-x1 0 Z C = 1 2 + (1 - 24) 1 dy de dx 0 Ao = - 2 == " dy cosode dx 0