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For the airfoil with the performance characteristics shown in the attached graph, determine the lift and drag at an angle of attack is the

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For the airfoil with the performance characteristics shown in the attached graph, determine the lift and drag at an angle of attack is the stall point 19.6. The airfoil has a chord length of 1.6m and a span of 6.4m. Perform the calculation at a speed of 250 km/h in the standard atmosphere at (a) 200m where p = 1.202 kg/m (b) 10,000m, p = 0.4135 kg/m

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