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Q1:Q4. Consider an aircraft flying in straight and level flight with total wing area 110 m², wing loading 2600 N/m² and a drag polar of 0.02 +0.06C2, at sea level. The aircraft engines can generate up to 1.8 times the thrust needed to maintain straight and level flight at 175 m/s. Calculate the climb rate that this aircraft could achieve. [10 marks] Q5. Summarise the ways in which the trim of an aircraft can be controlled by a pilot. [6 marks] Q6. Define the aerodynamic centre and why it's a useful point on an aircraft for analysing aerodynamic forces. [4 marks]See Answer
Q2:Project Part-1: 1. Implement and test (show execution of) the continuous-time component representing the dynamic model of a car given in the Textbook. Use the following values in the model: m= 1450 kg, k-63. Simulate the response for the case F-0, with initial conditions x(0)-0, v(0)=15 m/sec; and the case F-550 N with initial conditions x(0)=0, and v(0)=0. Use Trapezoidal discrete approximation of derivative with simulation step At-0.10 sec. Plot the component responses generated from your simulation. 2. Now add the effect of graded road to the above car model and regenerate the car responses to road grade of 0-5deg, and 0-10deg and the case F-550N with initial conditions x(0)=0, and v(0) 0 only. Plot the component responses generated by your simulation.See Answer

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