1. Aircraft Maximum Gross Weight [lbs] 3125 lbs 4. Wing Span [ft] 33 ft 6 in 5. Average Chord Length [ft] 5 ft 3 in 6. Wing Area 'S' [ft2] 181 ft squared 7. Find the Aspect Ratio 'AR' for your selected aircraft wing. (Use the wing span and average chord length from last week's module/from above. See also page 63 in your textbook.): AR Which is the wing span 33 ft 6 in divided by the average cord of 5 ft 3 in. AR = 176.4 8. CLmax for your airfoil: 9. Standard sea level Stall Speed 'Vs' for your aircraft [kts]: Find the appropriate drag polar curve for your airfoil selection 10. From the polar plot, find the CDmin value for your airfoil, i.e. the lowest value that the coefficient of drag 'Cd' (bottom scale in the online tool depiction) reaches. (Tip: for a numerical breakdown of the plotted curve, you can again select the \"Details\" link and directly read the lowest CD value in the table - third column, labeled \"CD\"): 0.05 let us for the remainder of our calculations assume that our aircraft is a Flying Wing type design and the total CDP for the aircraft is the same as the CDmin that we've just found. 0.05 Let us also assume that we are at standard sea level atmospheric conditions and that our wing has an efficiency factor of e = 0.82