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 W