A wing with a NACA 23015 airfoil profile has an aspect ratio of 10 and a taper ratio of 0.6. The lift coefficient chart for the NACA 23015 airfoil can be found on page 425 of the text. The required CL is 0.75. Assume that t = 8. Find: The induced drag coefficient (2 pts) a. b. The wing lift slope (2 pts) The geometric angle of attack (2 pts) . Remember to use the proper units (radians or degrees) for each equation. 3.6 3.2 2.8 2.4 2.0 1.6 1.2 438 /1131 0. -4 -8 -1.2 -4 -1.6 -2.0 -32 -24 -16 -8 8 16 24 32 Section angle of attack, ap, deg. NACA 23015 Wing Section Figure 5.2a Lift coefficient and moment coefficient about the quarter-chord for the NACA 23015 airfoil. Moment coefficient, c Section lift coefficient, e