Create the CM cg versus a plot a. List the aircraft you have been using for the previous assignments. List the wing area and the average wing chord. We will use the average wing chord as the reference chord in this homework. Aircraft: Airbus A320 Neo Wing area: 122.6 m Average wing chord: 3.42 ml b. Assume that the horizontal tail area is 20% of the wing area. Calculate the tail area St. c. Assume that the distance from the center of gravity to the aerodynamic center of the tail is 160% of the wing's average chord. Calculate lt. Calculate the tail volume VH. d. Using a tail aspect ratio of 5 and an efficiency e of 0.9, calculate the lift curve slope of the horizontal tail at. Assume that the tail airfoil has ao = 0.11 /deg e. We will assume that aL-o for the airplane is the aL-o of the NACA 23012 airfoil. Using the airfoil plots in the book, what is =0? f. We will assume that the aerodynamic center of the wing-body is located at 0.25c and the center of gravity is located at 0.4c. Calculate (h-hac,wb). [Remember that h and hac,wb are nondimensional] d g. Let us use it = -2, &o= 0, and = 0.35. We now have enough information to plot CMcg VS i. = - V at ( 1 de)] + Va (it + 0) CMacwb a = 0.1. The "a" in the equation is the lift curve slope of your wing CMCB Use CM ac,wb (found in Homework 5). Use Excel to plot CMcg from -o to at least a = 10. [Note: the letter "a" and the Greek letter alpha look very similar in the above equation. Make sure to use the correct values.] acm,cg h. Calculate either through your plot or by equation. Is the aircraft stable? + a(a =0) [h hacwb Why? From your plot, what is the trim angle of attack? You may have to extend your CMcg plot to find the answer. Remember that trim is when CMcg = 0. It is possible for there not to be a trim point. If this is the case, explain why.