piper cherokee wing area is 16m², span is 9.75m. totalweight is 1100kg. airfoil is NACA 65-415 and lift coefficient slopeis 0.1033 per degree. αL=0 is -1.5degree. Assume τ = 0.12. when airdensity is 1.23Kg/m³ and speed is 193Km/h. Determine the wing'sangle of attack