For the airfoil in Problem 4.11, calculate the value of the circulation

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°.