Consider tests of an unswept wing that spans the wind tunnel and whose airfoil section is NACA 23012. Since the wing model spans the test section, we will assume that the flow is two-dimensional. The chord of the model is 1.3 m. The test section conditions simulate a density at altitude of 3 km. The velocity in the test section is 360 km/hr. What is the lift per unit span (in N/m) that you would expect to measure when the angle of attack is 4o?