Problem 1 (30 Points) 5 Wing Tail 2n For the wing-tail combination shown in the sketch above (only the RHS of the airplane shown) the wing and tail surfaces have airfoils whose mean aerodynamic centers are at 25% chord locations. Assume that is 0.1, lift-curve slope for the wing is 0.1 /deg and for the tail is 0.07 /deg. Ignore fuselage and propulsion effects. You have done parts (a) and (b) of this problem in HW 3. You do not need to redo these parts. Instead use the solution to that problem to complete parts (c)- (f). For this configuration: (a) Determine (i) the wing m.a.c., c, (ii) the lateral distance (sideways distance) to the m.a.c., y, and (iii) x, the longitudinal distance (fore-aft distance) in meters of the wing aerodynamic center from the wing root leading edge, (b) Determine and V (c) Determine CL., the lift-curve slope of the airplane (wing + tail) in /deg. (d) Determine h (e) Determine h (f) Determine xxP in meters, i.e. the longitudinal (fore-and-aft) distance between the wing root leading edge and the neutral point.