Question 2 Given that the weight of an NACA 2409 plane is 1800 Lb with a span of 2.5 X 15 ft, and is flying with a velocity of 150 ft/s. Use the density of air 0.07882641b/ft3 , g 32.18 lb/ft2 Kinematic Viscosity is 1.48515 X 104 ft2 /s . Determine the Reynolds Number at the Back edge of the wing Coefficient of Lift Angle of attack (with relevant plots.) Drag coefficient for the wings infinite span (with relevant plots) Frictional Drag Coefficient Total Frictional Drag Drag on both wings. Speed that will cause the plan to stall. Provide a % comparison between frictional drag Coefficient and the Total drag coefficient, And or the total frictional drag and the drag on both wings. Briefly enumerate on methods to reduce. 15 ft 15 ft V = 150 ft/s 2.5 ft