Question 3 (10 marks) (2022 Paper) Question 3a The drag polar of a propeller powered aircraft is given as: C₂ = 0.0095 +0.038 x C² The aircraft weights 10,000 N and

has a wing area of 8 m². Question 3a(i) Analyse the speed of the aircraft at sea level when Power required is minimum. Question 3a(ii) If the engine power at sea level ISA condition is given as 80 kW. Due to the air traffic congestion near the aero dome, the aircraft was asked to climb at its maximum climb rate. Set up the appropriate method to calculate the following: (1) (2) (3) The climb speed. The maximum Rate of Climb. The corresponding climb angle. Question 3b During the test flight, the following data were measured by the test boom installed at the nose of the aircraft: OAT (outside air temperature) = 240 K P = 37,759 N/m² Po = 44,790 N/m² Question 3b(i) Apply the given data to calculate the Mach number of the aircraft. Question 3b(ii) Appraise the True Air Speed (TAS). EAS301 Copyright © 2022 Singapore University of Social Sciences (SUSS) TOA- July Semester 2022 Page 5 of 15/nQuestion 3b(iii) Appraise the Calibrate Air Speed (CAS) the pilot might read from the cockpit Air Speed Indicator (ASI). Question 3b(iv) Appraise the Dynamic Pressure at the condition of the flight.