find Di and Dp at (L/D)MAX:

information we have is

L = 10818

is the air density at sea level (approximately 0.002377 slugs/ft)

V is the airspeed 425.85ft/s S is the wing area (given as 227 ft)

C_L is the lift coefficient (given as 0.5)

Solve these problems: 1. A 10xxx-lb aircraft has an (L/D)MAX value of 9.8; find its minimum drag. For aircraft weight, enter the first three numbers of your phone number after "10" (For example, if your phone number starts with 412, enter aircraft weight as 10,412 lb). To find minimum drag, use equation 5.12 from the textbook, also provided here: Dmin = W 2. If the aircraft in Problem 11 has a wing area S=2xx ft and the value of Cy=0.5 at L/DMAX, find the sea level airspeed where DMIN occurs. (We will call this Vi.) For wing area, enter your age after "2" (for example, if you are 30, then you would enter S=230 ft ). Note: To solve for Vi, reference Table 2.1 Standard atmosphere table and Equation 4.4 (Velocity equation derived from the Lift equation). 3. For the aircraft in Problem 11, find Dj and Do at (L/D)MAX- 4. For the aircraft in Problem 11, complete the following table and plot Di, Do, and D, in Excel". V (V2 : VI) Dp = = Dmin (V2 : Vi)? (VI : V2)= Di = Dmin (Vi : V2)3 Dr = Dp + Di 125 150 172 200 300 400