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Engineering · Mechanical Engineering
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A supersonic aerofoil is shown in Figure 2. The angle of attack for the aerofoil is β. In this question α-20, β- 20, and the length of the chord is 1-1.0m. Upstream of the aerofoil, M2.2,p 20kPa, T,280K incident flo Figure 1. Schematic of flow past a thin aerofoil. a) Use the shock and expansion charts to calculate the lift and drag coefficients associated with the aerofoil. [10 marks] b) (i) Using the linear approximation described in equation 1, determine the the lift and drag coefficients (of figure 1) in terms of α, β and Mi . 8 marks] (ii) Compare this result against the values estimated in part (a) and discuss 2 marks] Useful Information : The relationship between pressure change and streamline deflection angle is 2Δν Equation 1 P1ul Mi -1 where symbols have their usual meaning.
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