An aircraft is configured such that the forces and moments are as shown in the diagram on slide 10 (Forces and moments). The wing is cambered and is oriented at a small positive angle of attack. The tailplane aerofoil is symmetrical and is oriented at a small negative angle of attack. a) Write down expressions for the wing lift coefficient and tailplane lift coefficient in terms of the angle of attack of the aircraft. b) Use your expressions from part (a) to show that this aircraft is stable when V For low speed (subsonic) aerofoils the aerodynamic centre is a quarter chord from leading edge. We previously used the non- dimensional lift and drag coefficients, we can produce a similar coefficient for pitching moment. M = (S)(C)(CM)