For the airfoil in Problem 4.11, calculate the value of the circulation around the airfoil.
Data from Problem 4.11:
Consider again the NACA 2412 airfoil discussed in Problem 4.10. The airfoil is flying at a velocity of 60 m/s at a standard altitude of 3 km (see Appendix D). The chord length of the airfoil is 2 m. Calculate the lift per unit span when the angle of attack is 4°.