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: W Dmin = (maz 2. If the aircraft in Problem 11 has a wing area S=2xx ft and the value of C-0.5 at L/DMAX, find the sea level airspeed where DMIN Occurs. (We will call this V.) 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 V, 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 D; and D, at (L/D)MAX. 4. For the aircraft in Problem 11, complete the following table and plot D, Dp, and Dt in Excel. (V V) Dp = Dmin (V2 V)(V V) V 125 150 172 200 300 400 Di = Dmin (V V)|DT = Dp + Di Once created, utilize your derived table and diagram data to answer the following associated questions: A. What are the minimum drag parameters for your aircraft? Minimum drag value D(min) Speed VD (min) at which minimum drag occurs Relationship between Dp and Di at D (min) . B. What are the maximum lift to drag ratio CL/CD parameters for your aircraft? . (CL/CD)max value Speed at which (CL/CD)max occurs C. Compare answers in A and B and comment on the findings. D. Explain which of your derived values will allow glide performance predictions for your aircraft and quantify best glide conditions with specific values. E. Explain the origin and effects of aircraft design and operating influences on induced drag. F. Explain sources of parasite drag and methods to reduce it. When doing any math, round to the nearest hundredth value (0.01), always include your units, and show your work for full credit. .