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**Q1:**Determine the semimajor axis and the eccentricity of the spacecraft's orbit whose position and velocity at a particular time is given asSee Answer**Q2:**and include any assumptions that have to be made to get this condition. Finally, discuss in a few sentences why a high-performance aircraft needs a capability for a maximised RoC, and give an example of the highest RoC that you can find. [10 marks]/nQ1. Explain in your own words why the stall speed of an aircraft is given by: W √ZPSC₁ Define all terms. Vstall v= Q2. An aircraft has a maximum lift coefficient of 1.65 with the flaps and slats up. The stalling speed for that level of trim is expected to be 99 m/s. The weight of the aircraft in cruise at this time is required to be 50500 Lbf, and the cruise altitude is 11.5 km. Find the wing area required to the aircraft these conditions. You may refer https://www.pdas.com/atmosTable2S1.html for any further data you may require. Show any rearrangements of equations used and also show all arithmetical working. support under to [10 marks] W Q3. Assume that an aircraft is climbing at a fixed angle of ascent and then proceed to show that the RoC is given by: 'L_max 1 ZPS ¹/2 [10 marks] T-1/2 (CDo + KC²) CL W (Ceo + KCB)) 3/2 C₁ Start your analysis using the RoC defined by v = V sin p. Define all terms used and show all steps in the analysis. Show then that the condition for maximum RoC is: T kCZ +CL-3CDo = 0 WSee Answer**Q3:**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**Q4:**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**Q5:**The orbit of the spacecraft whose poistion and velocity at a particular time is ellipse. You want to change thisSee Answer

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