Refer to the wind tunnel data for NACA-4412 (Figure-1), and specifically, we are only focusing on the RE=3e6 case. Keep in mind that the test data simulates a wing with infinite aspect ratio. a. Determine the following from the test data ac i. Cla = in rad-1 and deg-1 ii. L=0 iii. Cm,ac iv. Cpo in deg b. You are tasked with determining the basic aerodynamic characteristics of a rectangular wing with an AR of 6. Use the above information, along with Figure-2, determine the following: i. CLa == Cla =f Cla 1+ ; AR this formula assumes Ca is in 1/rad, and produces an CL in 1/rad. Now assuming our input Ca is in 1/deg, and we want an CL in 1/deg, what modification should you make of the equation? ii. What is the value of K in the formula CDwing CDO + KC, where K = 1 AR ; what is the value of e? iii. Using the drag formula above, determine the maximum L/D of the wing iv. Using the drag formula above, determine the optimal CL at which max L/D takes place. Furthermore, what is the geometric angle of attack needed to achieve the optimal C? 3.6 32 28 to 2.4 .024 2.0 Section lift coefficient, e Moment coefficient, c m A -5 -20 Section angle of attach, a deg 020 016 Section drag coefficient, 012 008 004 22 Moment coefficient, c 2 A 16 .8 0 1.0' 6 Standard flap deflected 60 Section lift coefficient, e. Figure 1 NACA 4412