Question 6 (Total 10 marks) (a) Consider a twin-engined jet aircraft with a conventional configuration, from which the aircraft data is summarised in Table Q2(a). (c) (d) m = 4,800 kg

S = 31.8 m² b = 15.90 m V = 55 ms-1 P = 1.225 kg m-3 Ye=0 CL = 0.46 Yv=-0.90 Ly = -0.07 Ny = 0.13 (ii) L = -0.35 N=-0.11 Y₂=0.21 L = 0.1 Nz= -0.05 Table Q2(a) During a landing approach, the airplane suffered a bird strike, where the rudder is stuck at maximum deflection of 15° (all derivatives above are per degree), analyse the following: (1) Assuming the aircraft maintain a steady flight with no roll and yaw motion. Starting from the dimensionless equation for the lateral-directional motion, analyse the balance in side force, roll and yaw moment equations, to show the following equations: C₁ +Y₂v+Y + Yę < =0 L₂V + L + L =0 N₂v + N₂ + N₂ = 0 Hence, or otherwise, analyse the required aileron deflection to main the steady flight and the corresponding slide slip angle. (b) Use a top view of an aircraft sketch, appraise the difference between slide slip angle and yaw angle. (iii) Appraise also the bank angle of the aircraft. Use side view of an aircraft sketch, appraise the difference between angle of attack and pitch angle. Use another separate side view of an aircraft sketch, explain why the flight path angle of the aircraft in a steady climb, is mostly like less than the pitch-up angle.