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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
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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