Complete the following:

(a) If the origin, o, is located at the wing tip and the leading & trailing edge curve is given above, find the constant c at the wing root and then calculate the chord of the wing at position 2 and position 3 as indicated in figure 1. (Marks Breakdown: find constant c, chord pos. 2 [2], chord pos. 3 [2], workings shown [4])

(b) (i) Develop expressions for the shear force and bending moment distribution along the length of the wing as a function of distance, x, measured from the tip.

(ii) Produce accurate sketches (or plot) the shear force and bending moment distribution along the length of the wing as a function of distance, x, measured from the tip. Show values at the wing root and tip. (Marks Breakdown: (i) shear force [3 marks], bending mom. [3], workings shown [4]; (ii) shear plot [3], bending plot [3], tip/root values [4])

(c) Calculate the bending stresses in the extreme fibre (upper surface) at the tip (position 1) and position 3 on the wing as indicated in figure 1. (Marks Breakdown: appropriate equations applied [5 marks], illustration of stress distribution [3], constants clearly defined [3], algebraic expression for stress derived [5], stress values calculated at both positions [5], workings shown [4])

(d) Calculate the shear stress at the position 2 on the wing as indicated in figure 1. (Marks Breakdown: appropriate equations applied [2 marks], constants clearly defined [3], algebraic expressions for stress derived [4], stress value calculated [2], workings shown [4])

(e) An engine with a mass of 200kg is mounted from the lower surface of the wing at position 3. Repeat part (b) for this loading case - include the values of shear force and bending moment at the engine mount position as well as the root and tip on your diagrams. (Marks Breakdown: shear force, bending mom. [4], workings shown [4], shear plot [5], bending plot [5], tip/root values [4], values at
pos. 3 [4])