Consider an airplane that weighs 14,700 n and cruises in level flight at 300 km/hr at an altitude of 3000 m (rho = 0.90926 kg/m3 ). the wing has a surface area of 17.0 m2 and an aspect ratio of 6.2. assume that the lift coefficient is a linear function of the angle of attack and that αl0 = -1.2º. if the load distribution is elliptic, calculate the value of the circulation in the plane of symmetry (γ0), the downwash velocity, the induced drag coeff

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which ordered pair is not in the solution

y > -1/2x + 5

y ≤ 3x - 2

a) (5,3) b) (4,3)

c) (3,4) d) (4,4)