Consider an NACA 2412 airfoil (data given in Fig. 2.6) with chord of 1.5 m at an angle of attack of 4°. For a free-stream velocity of 30 m/s at standard sea-level conditions, calculate the lift and drag per unit span. Note: The viscosity coefficient at standard sea-level conditions is 1.7894 × 10−5kg/(m·s).
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