Engineering, 15.04.2020 05:14, brandonleekenyon

(a) Using Thin Airfoil Theory, write down the equation of lift coefficient for Symmetric airfoil Cambered airfoil.
(b) Comment on the location of aerodynamic centre and centre of pressure for both types of airfoil i. e. symmetric and cambered.
(c) Consider an NACA 0012 airfoil with a 2-m chord in an airstream with a velocity of 50 m/s at standard sea-level conditions. If the lift per unit span is 1353 N, what is the angle of attack, using Thin airfoil theory?

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(a) Using Thin Airfoil Theory, write down the equation of lift coefficient for Symmetric airfoil Cam...