A series of wind tunnel tests were performed on a 12th scale model aircraft. Assume that the constants in the relationship between angle of attack and coefficient of lift and the drag equation are all independent of Reynold's number. The following table of results were obtained from the first set of tests. The speed stated is the equivalent air speed and the coefficient of pitching moment is taken about the leading edge of the wing. Angle of attack (degrees) 1 0.315 0.03248 3 0.495 0.03613 5 25 0.675 0.04139 The model aircraft has a span of 1 m and an aspect ratio of 8. (i) (ii) (iii) Speed (m s-) (f) What are the values of the following quantities? Lift in the test at an angle attack of 3. [5 Marks] Pitching moment about the leading edge in the test at an angle of attack of 1. [3 Marks] [5 Marks] (iv) 15 20 Coefficient of Coefficient of lift drag Coefficient of pitching moment -0.6044 -0.9212 -1.238 Zero lift angle of attack? Distance from the leading edge to the aerodynamic centre. [7 Marks]