The mean camber line of a NACA four-digit airfoil is given by S# [2P (9) -...

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The mean camber line of a NACA four-digit airfoil is given by S# [2P (9) - (9)²] m (¹² [(1 − 2p) + 2p (²) − (9²] for 0≤x≤ pc, for pc ≤ x ≤ c where c is the chord, m is the maximum camber (100m is the first of the four digits in the NACA xxxx classification) and p is the location of the maximum camber (10p is the second digit). Using thin airfoil theory, calculate for NACA 2415 airfoil (a) The angle of attack for zero lift a=0 (b) The lift coefficient c₂ when a = 3° The mean camber line of a NACA four-digit airfoil is given by S# [2P (9) - (9)²] m (¹² [(1 − 2p) + 2p (²) − (9²] for 0≤x≤ pc, for pc ≤ x ≤ c where c is the chord, m is the maximum camber (100m is the first of the four digits in the NACA xxxx classification) and p is the location of the maximum camber (10p is the second digit). Using thin airfoil theory, calculate for NACA 2415 airfoil (a) The angle of attack for zero lift a=0 (b) The lift coefficient c₂ when a = 3°