A NACA 2415 airfoil with a 0.6 m chord and a 2.5 meter span is being tested in a wind tunnel at standard sea-level conditions and a test section velocity of 175 m/s and an angle of attack of 8 degrees. What is the airfoil's lift curve slope, and how much lift is this test specimen generating? (Note: a) data on this airfoil appears in your textbook on pages 466-467, b) recall that, for conditions greater than M=0.3 (about 100 m/s in this case), corrections for compressibility must be made).