1. Consider an NACA 1412 airfoil at an angle of attack of 4 °. If the free-stream Mach number is 0.8, calculate the lift coefficient. 2. An NACA 4415 airfoil is mounted in a high-speed subsonic wind tunnel. The lift coefficient is measured as 0.85. If the test-section Mach number is 0.7, at what angle of attack is the airfoil?

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