Consider a NACA 2415 airfoil in low-speed incompressible flow at Re = 9 10 ⁶ and zero degrees angle of attack. The boundary layer starts out as laminar and then transitions to turbulent at some point downstream of the leading edge. Assume the critical Reynolds number for transition is 650,000 for the NACA 2415 airfoil. Calculate the skin friction drag coefficient, percentage of friction drag, and the percentage of pressure drag. Refer to the standard values for a NACA 2415 airfoil from the graph given below.

36 321 28 era 2 10 241 .024 20 1020 26 016 Section drag coefficient, 12 012 008 Section will coollicient, 004 -8 Morrent coefficient - o 30.10 D60 O 90 A 6.0 de position ac yle .24 1.014 246 +013 2481013 Stordord rouess Moment -16 -24 24 16 -12 8 2 16 -18 o & 16 Section angle of affact, a deg NACA 2415 Wing Section - O Section lift coolficient, NACA 2415 Wing Section continued) 36 321 28 era 2 10 241 .024 20 1020 26 016 Section drag coefficient, 12 012 008 Section will coollicient, 004 -8 Morrent coefficient - o 30.10 D60 O 90 A 6.0 de position ac yle .24 1.014 246 +013 2481013 Stordord rouess Moment -16 -24 24 16 -12 8 2 16 -18 o & 16 Section angle of affact, a deg NACA 2415 Wing Section - O Section lift coolficient, NACA 2415 Wing Section continued)