Q2. Thin aerofoil theory predicts the lift and moment coefficients to be given by: CL=2(A0+21A1)CMLE=2(A0+A121A2) with A0=10dxdydAn=20dxdycos(n)dcx=21(1cos) where dxdy is the slope of the mean camber line. Derive an equation for the angle of zero lift, 0. Determine the expressions for CL,CMLE and 0 for an aerofoil with mean camber line: cy=4[cx(cx)2] Note: for integer m and n:0cos(mx)cos(nx)dx=/2 when m=n and zero otherwise. Plot the pressure difference coefficient, (1/2)V2p as a function of x/c along the camber line for =/60 and angles of incidence of 6,0 and 6. Explain the results