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drag polarxlsx - Fuselage Nose Length y­location diameter...

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Unformatted text preview: Fuselage Nose Length y­location diameter Number of Passengers Number of Flight Crew Mcruise Center of Gravity x­location Neutral Point x­location Static Margin #NUM! Chord Empty Weight Total Weight Thrust To Weight Ratio Wing Loading 11 ­2 0 Fuselage Empannage End 27 0 7 13 0 7 9 2 0.800 #NUM! ft #NUM! ft #NUM! #NUM! #NUM! lb #NUM! lb 0.3632 92.63 0 2 0 Wing Area Leading Edge Angle Sweep Angle Taper Ratio Aspect Ratio x­Location y­Location Main Wing #NUM! 30 #NUM! 0.5 7.8 22.6 ­3 NACA Wing Canard 0 25 0 0.6 3 3 ­2 Yehudi 30 #NUM! #NUM! 0 12 #NUM! ­3 Tail 100 25 21.78 0.5 5 37 3.5 2414 Vertical 100 30 22.33 0.5 2 36 4 2 0 -2 0 0.6 2 4 6 8 10 12 13 3 -7 0 40 30 20 10 0 -10 -20 -30 -40 0 15 5 -5 -30 5 10 15 20 25 30 35 40 45 50 5 10 15 20 25 30 35 40 45 50 0.5 0.4 0.3 0.2 0.1 Top of climb ( 1g steady, l evel flight, M = 0.80 @ h=45K, service ceiling) Subsonic 2g manuever, 250kts @ h =10K T akeoff ground roll 4000 ft @ h = 5K, +15° hot day Landing ground roll 2500 ft @ h = 5K, +15° hot day Second segment climb gradient a bove h = 5K, +15° hot day W0/S & TSL/ W0 Value -20 -10 0 10 20 30 0 50 60 70 80 90 100 110 120 130 Engine Unducted Fan Length Location x­location y­location z­location Thrust Performance Weight Number of Engine 2 38 3.5 7.5 3 40 0 7.5 4 4 43 0 7.5 2000 237 0 0 7.5 lbf lbs 2 0.5 0 7.5 4 47 47.5 Misson Sketch 55000 35000 15000 -5000 -500 diameter 2.09 4.5 2.09 0 500 1000 1500 2000 2500 3000 0 12 Flight Time of climb steady, el flight, M .80 @ 45K, sere ceiling) sonic 2g nuever, kts @ h 0K e off und roll 0 ft @ h = +15° hot ding und roll 0 ft @ h = +15° hot o nd segnt climb dient ve h = 5K, 5° hot day /S & TSL/ Value Fuel Consumption Area 2.662 ft^2 Diameter 2.089 ft Length 4.26 ft Volume 5.89 ft^3 Unducted Fan Number of Engine 1 Length 2 3 4 0 0.5 x­location 40 42 45 49 49.5 y­location 0 0 0 0 0 z­location 6.5 6.5 6.5 6.5 6.5 diameter ### 5 5 ### 4 Thrust #NUM! lbf Weight #NUM! lbs Area #NUM! ft^2 Diameter #NUM! ft Length #NUM! ft Volume #NUM! ft^3 Misson Taxi Takeoff Climb Cruise Loiter Attept to Land Climb Divert Distance 0.76 2 30 3409.8 20 0.95 16 200 Altitude 0 10000 40000 45000 16000 2000 10000 40000 Acculative Distance 0.76 2.76 32.76 3442.56 3462.56 3463.51 3479.51 3679.51 A/C Weight#NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! Fuel Weight #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! Location CG Travel 31000 29000 27000 25000 23000 Weight 21000 19000 17000 15000 25 30 35 Location Take Off Gear up Fuselage Tank Wing Tank Gear Down Land Reserve Fuel Passenger Off #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! Performance Travel Information Fuel Density 6.8 4.42 #NUM! 7.76 50 8.37 18.08 20.80 lb/Gal Fuel Price Mission Fuel Price Flight Time Wind Flight Time Increase in Mile $/Gallon $ hrs ft/s hrs nmi CG miles Weight 40 2000 2500 Loiter 3000 3500 4000 4500 Land 20 0.49 16000 2000 3699.51 3700 #NUM! #NUM! #NUM! #NUM! ravel 40 Location 45 50 Crew Off Add Fuel Add Crew Add Passenger Max Min #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! Length CenterLine Start diameter Volume Wetted Area 15 10 5 0 -5 -10 -15 0 10 5 0 -5 -10 10 5 0 -5 -30 0 Tail Yehudi Wing Area Sweep Angle Taper Ratio Aspect Ratio x­Location y­Location b/2 C1+C2 d C1 C2 C1quarter C2quarter 5 10 15 20 25 30 35 40 45 50 C1qLocation C2qLoaction Sweep angle angle Wetted Area sweep correction 5 10 15 20 25 30 35 40 45 50 Form Factor interference factor Mean Chord Length Center of Pressure Partial Lift -20 -10 0 10 20 30 Moment CenterLine Total Lift x y radius y­top y­bottom z­top z­bottom #NUM! 0 0 ­2 0 ­2 ­2 0 0 1 2.2 ­1.6 0.7 ­0.9 ­2.3 0.7 ­0.7 2 4.4 ­1.2 1.4 0.2 ­2.6 1.4 ­1.4 3 6.6 ­0.8 2.1 1.3 ­2.9 2.1 ­2.1 4 8.8 ­0.4 2.8 2.4 ­3.2 2.8 ­2.8 5 11 0 3.5 3.5 ­3.5 3.5 ­3.5 6 11 0 3.5 3.5 ­3.5 3.5 ­3.5 7 16.4 0 3.5 3.5 ­3.5 3.5 ­3.5 8 21.8 0 3.5 3.5 ­3.5 3.5 ­3.5 9 27.2 0 3.5 3.5 ­3.5 3.5 ­3.5 10 32.6 0 3.5 3.5 ­3.5 3.5 ­3.5 11 38 0 3.5 3.5 ­3.5 3.5 ­3.5 12 38 0 3.5 3.5 ­3.5 3.5 ­3.5 13 40.6 0.4 2.8 3.2 ­2.4 2.8 ­2.8 Canard Wing Fuselage mpannage E End 11 27 13 0 total length 51 x 0 11 38 51 diameter 7 y ­2 0 0 2 Fineness ratio 7.29 d 0 7 7 0 wetted area 922.6 141.11 ### 166.77 form factor 1.17 126.93 593.76 148.03 interference factor 1 0 Nose Fuselage Wing Fuselage Nose radius 0y ­2 0 Point # Angle y­position­position-1 z 0 0 0 ­2 -2 1 0.39 0 ­2 -3 2 0.79 0 ­2 0 3 1.18 0 ­2 4 1.57 0 ­2 5 1.96 0 ­2 6 2.36 0 ­2 7 2.75 0 ­2 8 3.14 0 ­2 9 3.53 0 ­2 10 3.93 0 ­2 11 4.32 0 ­2 12 4.71 0 ­2 13 5.11 0 ­2 14 5.5 0 ­2 15 5.89 0 ­2 16 6.28 0 ­2 radius 0.7 y ­1.6 0 Point # Angle y­position­position z -1 0 0 0 ­0.9 -2 1 0.39 0.27 ­0.95 -3 2 0.79 0.49 ­1.11 -1 3 1.18 0.65 ­1.33 4 1.57 0.7 ­1.6 5 1.96 0.65 ­1.87 6 2.36 0.49 ­2.09 7 2.75 0.27 ­2.25 8 3.14 0 ­2.3 9 3.53 ­0.27 ­2.25 10 3.93 ­0.49 ­2.09 11 4.32 ­0.65 ­1.87 12 4.71 ­0.7 ­1.6 13 5.11 ­0.65 ­1.33 14 5.5 ­0.49 ­1.11 15 5.89 ­0.27 ­0.95 16 6.28 0 ­0.9 radius 1.4 y ­1.2 2 0 -2 -4 -2 0.5 1 Section 0 Vertical Colum nE Tail 14 15 16 17 43.2 45.8 48.4 51 0.8 1.2 1.6 2 2.1 1.4 0.7 0 2.9 2.6 2.3 2 ­1.3 ­0.2 0.9 2 2.1 1.4 0.7 0 ­2.1 ­1.4 ­0.7 0 Tail Yehudi 1 0 Coefficient of Lift Colu mn E 0 1 -0 Section 1 Colum nE 0 2 2 Section 4 Point # Angle y­position­position 0 z 0 0 0 0.2 -2 1 0.39 0.54 0.09 -4 2 0.79 0.99 ­0.21 -2 0 3 1.18 1.29 ­0.66 4 1.57 1.4 ­1.2 5 1.96 1.29 ­1.74 6 2.36 0.99 ­2.19 7 2.75 0.54 ­2.49 8 3.14 0 ­2.6 9 3.53 ­0.54 ­2.49 10 3.93 ­0.99 ­2.19 11 4.32 ­1.29 ­1.74 12 4.71 ­1.4 ­1.2 13 5.11 ­1.29 ­0.66 14 5.5 ­0.99 ­0.21 15 5.89 ­0.54 0.09 16 6.28 0 0.2 radius 2.1 y ­0.8 2 Point # Angle y­position­position 0 z 0 0 0 1.3 -2 1 0.39 0.8 1.14 -4 2 0.79 1.48 0.68 -5 0 3 1.18 1.94 0 4 1.57 2.1 ­0.8 5 1.96 1.94 ­1.6 6 2.36 1.48 ­2.28 7 2.75 0.8 ­2.74 8 3.14 0 ­2.9 9 3.53 ­0.8 ­2.74 10 3.93 ­1.48 ­2.28 11 4.32 ­1.94 ­1.6 12 4.71 ­2.1 ­0.8 13 5.11 ­1.94 0 14 5.5 ­1.48 0.68 15 5.89 ­0.8 1.14 16 6.28 0 1.3 radius 2.8 y ­0.4 5 Point # Angle y­position­position z 0 0 0 2.4 0 1 0.39 1.07 2.19 -5 2 0.79 1.98 1.58 -4 -2 0 3 1.18 2.59 0.67 4 1.57 2.8 ­0.4 5 1.96 2.59 ­1.47 Colum nE 2 Section 2 Colu mn E 5 Section 3 Colu mn E 2 4 6 2.36 1.98 ­2.38 7 2.75 1.07 ­2.99 8 3.14 0 ­3.2 9 3.53 ­1.07 ­2.99 10 3.93 ­1.98 ­2.38 11 4.32 ­2.59 ­1.47 12 4.71 ­2.8 ­0.4 13 5.11 ­2.59 0.67 14 5.5 ­1.98 1.58 15 5.89 ­1.07 2.19 16 6.28 0 2.4 radius 3.5 y 05 Point # Angle y­position­position z 0 0 0 3.5 0 1 0.39 1.34 3.23 -5 2 0.79 2.47 2.47 -4 -2 0 3 1.18 3.23 1.34 4 1.57 3.5 0 5 1.96 3.23 ­1.34 6 2.36 2.47 ­2.47 7 2.75 1.34 ­3.23 8 3.14 0 ­3.5 9 3.53 ­1.34 ­3.23 10 3.93 ­2.47 ­2.47 11 4.32 ­3.23 ­1.34 12 4.71 ­3.5 0 13 5.11 ­3.23 1.34 14 5.5 ­2.47 2.47 15 5.89 ­1.34 3.23 16 6.28 0 3.5 radius 3.5 y 05 Point # Angle y­position­position z 0 0 0 3.5 0 1 0.39 1.34 3.23 -5 2 0.79 2.47 2.47 -4 -2 0 3 1.18 3.23 1.34 4 1.57 3.5 0 5 1.96 3.23 ­1.34 6 2.36 2.47 ­2.47 7 2.75 1.34 ­3.23 8 3.14 0 ­3.5 9 3.53 ­1.34 ­3.23 10 3.93 ­2.47 ­2.47 11 4.32 ­3.23 ­1.34 12 4.71 ­3.5 0 Section 4 Colu mn E 2 4 Section 5 Colu mn E 2 4 Section 6 13 5.11 ­3.23 1.34 14 5.5 ­2.47 2.47 15 5.89 ­1.34 3.23 16 6.28 0 3.5 radius 3.5 y 05 Point # Angle y­position­position z 0 0 0 3.5 0 1 0.39 1.34 3.23 -5 2 0.79 2.47 2.47 -4 -2 0 2 4 3 1.18 3.23 1.34 4 1.57 3.5 0 5 1.96 3.23 ­1.34 6 2.36 2.47 ­2.47 7 2.75 1.34 ­3.23 8 3.14 0 ­3.5 9 3.53 ­1.34 ­3.23 10 3.93 ­2.47 ­2.47 11 4.32 ­3.23 ­1.34 12 4.71 ­3.5 0 13 5.11 ­3.23 1.34 14 5.5 ­2.47 2.47 15 5.89 ­1.34 3.23 16 6.28 0 3.5 radius 3.5 y 05 Point # Angle y­position­position z 0 0 0 3.5 0 1 0.39 1.34 3.23 -5 2 0.79 2.47 2.47 -4 -2 0 2 4 3 1.18 3.23 1.34 4 1.57 3.5 0 5 1.96 3.23 ­1.34 6 2.36 2.47 ­2.47 7 2.75 1.34 ­3.23 8 3.14 0 ­3.5 9 3.53 ­1.34 ­3.23 10 3.93 ­2.47 ­2.47 11 4.32 ­3.23 ­1.34 12 4.71 ­3.5 0 13 5.11 ­3.23 1.34 14 5.5 ­2.47 2.47 15 5.89 ­1.34 3.23 16 6.28 0 3.5 radius 3.5 y 05 Point # Angle y­position­position z 0 0 0 3.5 0 -5 -4 -2 0 2 4 Colu mn E Section 7 Colum nE Section 8 Colu mn E 5 0 Colu mn E 2 4 Section 11 1 0.39 1.34 3.23 -5 2 0.79 2.47 2.47 -4 -2 0 3 1.18 3.23 1.34 4 1.57 3.5 0 5 1.96 3.23 ­1.34 6 2.36 2.47 ­2.47 7 2.75 1.34 ­3.23 8 3.14 0 ­3.5 9 3.53 ­1.34 ­3.23 10 3.93 ­2.47 ­2.47 11 4.32 ­3.23 ­1.34 12 4.71 ­3.5 0 13 5.11 ­3.23 1.34 14 5.5 ­2.47 2.47 15 5.89 ­1.34 3.23 16 6.28 0 3.5 radius 3.5 y 05 Point # Angle y­position­position z 0 0 0 3.5 0 1 0.39 1.34 3.23 -5 2 0.79 2.47 2.47 -4 -2 0 3 1.18 3.23 1.34 4 1.57 3.5 0 5 1.96 3.23 ­1.34 6 2.36 2.47 ­2.47 7 2.75 1.34 ­3.23 8 3.14 0 ­3.5 9 3.53 ­1.34 ­3.23 10 3.93 ­2.47 ­2.47 11 4.32 ­3.23 ­1.34 12 4.71 ­3.5 0 13 5.11 ­3.23 1.34 14 5.5 ­2.47 2.47 15 5.89 ­1.34 3.23 16 6.28 0 3.5 radius 3.5 y 05 Point # Angle y­position­position z 0 0 0 3.5 0 1 0.39 1.34 3.23 -5 2 0.79 2.47 2.47 -4 -2 0 3 1.18 3.23 1.34 4 1.57 3.5 0 5 1.96 3.23 ­1.34 6 2.36 2.47 ­2.47 7 2.75 1.34 ­3.23 Section 9 Colu mn E 2 4 Section 10 Colu mn E 2 4 Section 11 8 3.14 0 ­3.5 9 3.53 ­1.34 ­3.23 10 3.93 ­2.47 ­2.47 11 4.32 ­3.23 ­1.34 12 4.71 ­3.5 0 13 5.11 ­3.23 1.34 14 5.5 ­2.47 2.47 15 5.89 ­1.34 3.23 16 6.28 0 3.5 radius 3.5 y 05 Point # Angle y­position­position z 0 0 0 3.5 0 1 0.39 1.34 3.23 -5 2 0.79 2.47 2.47 -4 -2 0 3 1.18 3.23 1.34 4 1.57 3.5 0 5 1.96 3.23 ­1.34 6 2.36 2.47 ­2.47 7 2.75 1.34 ­3.23 8 3.14 0 ­3.5 9 3.53 ­1.34 ­3.23 10 3.93 ­2.47 ­2.47 11 4.32 ­3.23 ­1.34 12 4.71 ­3.5 0 13 5.11 ­3.23 1.34 14 5.5 ­2.47 2.47 15 5.89 ­1.34 3.23 16 6.28 0 3.5 radius 2.8 y 0.4 5 Point # Angle y­position­position z 0 0 0 3.2 0 1 0.39 1.07 2.99 -5 2 0.79 1.98 2.38 -4 -2 0 3 1.18 2.59 1.47 4 1.57 2.8 0.4 5 1.96 2.59 ­0.67 6 2.36 1.98 ­1.58 7 2.75 1.07 ­2.19 8 3.14 0 ­2.4 9 3.53 ­1.07 ­2.19 10 3.93 ­1.98 ­1.58 11 4.32 ­2.59 ­0.67 12 4.71 ­2.8 0.4 13 5.11 ­2.59 1.47 14 5.5 ­1.98 2.38 Colu mn E 2 4 Section 12 Colu mn E 2 4 Section 13 15 5.89 ­1.07 2.99 16 6.28 0 3.2 radius 2.1 y 0.8 4 Point # Angle y­position­position 2 z 0 0 0 2.9 0 1 0.39 0.8 2.74 -2 2 0.79 1.48 2.28 -5 3 1.18 1.94 1.6 4 1.57 2.1 0.8 5 1.96 1.94 0 6 2.36 1.48 ­0.68 7 2.75 0.8 ­1.14 8 3.14 0 ­1.3 9 3.53 ­0.8 ­1.14 10 3.93 ­1.48 ­0.68 11 4.32 ­1.94 0 12 4.71 ­2.1 0.8 13 5.11 ­1.94 1.6 14 5.5 ­1.48 2.28 15 5.89 ­0.8 2.74 16 6.28 0 2.9 radius 1.4 y 1.2 4 Point # Angle y­position­position 2 z 0 0 0 2.6 0 1 0.39 0.54 2.49 -2 2 0.79 0.99 2.19 -2 3 1.18 1.29 1.74 4 1.57 1.4 1.2 5 1.96 1.29 0.66 6 2.36 0.99 0.21 7 2.75 0.54 ­0.09 8 3.14 0 ­0.2 9 3.53 ­0.54 ­0.09 10 3.93 ­0.99 0.21 11 4.32 ­1.29 0.66 12 4.71 ­1.4 1.2 13 5.11 ­1.29 1.74 14 5.5 ­0.99 2.19 15 5.89 ­0.54 2.49 16 6.28 0 2.6 radius 0.7 y 1.6 3 Point # Angle y­position­position z 2 0 0 0 2.3 1 1 0.39 0.27 2.25 0 2 0.79 0.49 2.09 -1 Colu mn E 0 5 Section 14 Colu mn E 0 2 Section 15 Colu mn E 0 1 16 2 1 0 -1 0 1 Colu mn E 3 1.18 0.65 1.87 4 1.57 0.7 1.6 5 1.96 0.65 1.33 6 2.36 0.49 1.11 7 2.75 0.27 0.95 8 3.14 0 0.9 9 3.53 ­0.27 0.95 10 3.93 ­0.49 1.11 11 4.32 ­0.65 1.33 12 4.71 ­0.7 1.6 13 5.11 ­0.65 1.87 14 5.5 ­0.49 2.09 15 5.89 ­0.27 2.25 16 6.28 0 2.3 radius 0y 23 Point # Angle y­position­position z 2 0 0 0 21 1 0.39 0 2 0 2 0.79 0 20 3 1.18 0 2 4 1.57 0 2 5 1.96 0 2 6 2.36 0 2 7 2.75 0 2 8 3.14 0 2 9 3.53 0 2 10 3.93 0 2 11 4.32 0 2 12 4.71 0 2 13 5.11 0 2 14 5.5 0 2 15 5.89 0 2 16 6.28 0 2 Section 16 Colu mn E 0.5 1 Section 17 Wing Canard Yehudi Tail Vertical #NUM! 0 30 100 100 30 25 #NUM! 25 30 0.5 0.6 0 0.5 0.5 7.8 3 12 5 2 22.6 3 #NUM! 37 36 ­3 ­2 ­3 3.5 0 #NUM! 0 9.49 11.18 7.07 #NUM! #DIV/0! 3.16 8.94 14.14 #NUM! 0 #NUM! 5.21 4.08 #NUM! #DIV/0! 3.16 5.96 9.43 #NUM! #DIV/0! 0 2.98 4.71 #NUM! #DIV/0! 0.79 1.49 2.36 #NUM! #DIV/0! 0 0.75 1.18 #NUM! #DIV/0! #NUM! 38.49 38.36 #NUM! #DIV/0! #NUM! 42.96 41.26 #NUM! #DIV/0! #NUM! 21.78 22.33 #NUM! #NUM! 0 61.2 204 204 #NUM! #DIV/0! #NUM! 1.89 1.87 #NUM! #NUM! #NUM! #NUM! #NUM! 1 1 1 1 1 #NUM! #DIV/0! 1.58 4.47 7.07 #NUM! #DIV/0! #NUM! 40.72 39.81 #NUM! #NUM! #NUM! #NUM! #NUM! 0 #NUM! #NUM! Total Lift Total Moment AeroDynamic Center #NUM! #NUM! #NUM! x y z neg­z Wing Engines Unducted Fan Number of Engine 1 Length Engine 2 3 2 3 4 x 38 40 43 y 3.5 3.5 3.5 CenterLine z 7.5 7.5 7.5 diameter d 2.09 4 4.5 Wetted Area 13.13 37.7 56.55 Form Factor interference factor Jet x y CenterLine z diameter d Wetted Area Length 2 3 4 40 42 45 0 0 0 0 0 0 ### 5 5 ### 58.9 78.54 1 Number of Engine 2 3 Engine 10 5 0 -5 20 20 10 0 -10 25 30 35 40 45 50 55 A B C D A B C D A B x 22.6 #NUM! #NUM! #NUM! 3 3 #DIV/0! #DIV/0! #NUM! #NUM! y ­3 ­3 ­3 ­3 ­2 ­2 ­2 ­2 ­3 ­3 z 0 #NUM! #NUM! 0 x y z 0 -20 #NUM! 0 5 10 15 20 25 30 35 40 #NUM! 8 0 6 neg­z 0 04 0 02 0 00 0 0 -10 -8 -6 -4 -2 0 2 4 6 neg­z x y z radius y­top y­bottom 0 0 38 3.5 ### 0 3.5 3.5 9.49 ­9.49 38 3.5 ### 1.04 4.54 2.46 45 50 8 10 C D A B C D A B C D x #NUM! #NUM! 37 42.21 45.19 42.96 36 40.08 44.8 45.43 1 1.5 y ­3 ­3 3.5 3.5 3.5 3.5 0 7.07 7.07 0 z x y z ­9.49 0 neg­z 0 0 11.18 ­11.18 11.18 ­11.18 0 0 0 0 0 0 9.49 0 40 43 47 47 38 38 40 43 47 47 radius Point # 3.5 ### 3.5 ### 3.5 ### 3.5 ### 3.5 ### 3.5 ### 3.5 ### 3.5 ### 3.5 ### 3.5 ### 2 2.25 1.04 0 0 1.04 2 2.25 1.04 0 5.5 5.75 4.54 3.5 3.5 4.54 5.5 5.75 4.54 3.5 1.5 1.25 2.46 3.5 3.5 2.46 1.5 1.25 2.46 3.5 Drag Po 0.5 Coefficient of Lift 0 -0.5 -1 0 0.02 ### x y z Angle x­position y­position z­position 00 38 3.5 8.54 1 ### 38 3.9 8.47 2 ### 38 4.24 8.24 3 ### 38 4.47 7.9 4 ### 38 4.54 7.5 5 ### 38 4.47 7.1 6 ### 38 4.24 6.76 7 ### 38 3.9 6.53 8 ### 38 3.5 6.46 9 ### 38 3.1 6.53 10 ### 38 2.76 6.76 11 ### 38 2.53 7.1 12 ### 38 2.46 7.5 13 ### 38 2.53 7.9 14 ### 38 2.76 8.24 15 ### 38 3.1 8.47 16 ### 38 3.5 8.54 radius 2 Point # Angle 00 40 3.5 9.5 1 ### 40 4.27 9.35 2 ### 40 4.91 8.91 3 ### 40 5.35 8.27 4 ### 40 5.5 7.5 5 40 5.35 6.73 0.04 ### 0.06 6 ### 40 4.91 6.09 Coefficient of 7 ### 40 4.27 5.65 8 ### 40 3.5 5.5 9 ### 40 2.73 5.65 10 ### 40 2.09 6.09 11 ### 40 1.65 6.73 Section 2 Section 1 Se radius Point # radius Point # radius Point # 12 ### 13 ### 14 ### 15 ### 16 ### ### Angle 00 1 ### 2 ### 3 ### 4 ### 5 ### 6 ### 7 ### 8 ### 9 ### 10 ### 11 ### 12 ### 13 ### 14 ### 15 ### 16 ### ### Angle 00 1 ### 2 ### 3 ### 4 ### 5 ### 6 ### 7 ### 8 ### 9 ### 10 ### 11 ### 12 ### 13 ### 14 ### 15 ### 16 ### 0 Angle 40 1.5 7.5 40 1.65 8.27 40 2.09 8.91 40 2.73 9.35 40 3.5 9.5 43 43 43 43 43 43 43 43 43 43 43 43 43 43 43 43 43 3.5 4.36 5.09 5.58 5.75 5.58 5.09 4.36 3.5 2.64 1.91 1.42 1.25 1.42 1.91 2.64 3.5 9.75 9.58 9.09 8.36 7.5 6.64 5.91 5.42 5.25 5.42 5.91 6.64 7.5 8.36 9.09 9.58 9.75 Section 3 47 47 47 47 47 47 47 47 47 47 47 47 47 47 47 47 47 3.5 3.9 4.24 4.47 4.54 4.47 4.24 3.9 3.5 3.1 2.76 2.53 2.46 2.53 2.76 3.1 3.5 8.54 8.47 8.24 7.9 7.5 7.1 6.76 6.53 6.46 6.53 6.76 7.1 7.5 7.9 8.24 8.47 8.54 Section 4 00 1 ### 2 ### 3 ### 4 ### 5 ### 6 ### 7 ### 8 ### 9 ### 10 ### 11 ### 12 ### 13 ### 14 ### 15 ### 16 ### y 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 x Prop 40 40 42 45 49 49 z radius y­top y­bottom 00 0 0 0 0 0 ### ### ### 00 2.5 2.5 ­2.5 00 2.5 2.5 ­2.5 0 0 ### ### ### 00 0 0 0 ### x y z Angle x­position y­position z­position 00 40 ### ### 1 ### 40 ### ### 2 ### 40 ### ### 3 ### 40 ### ### 4 ### 40 ### ### 5 ### 40 ### ### 6 ### 40 ### ### 7 ### 40 ### ### 8 ### 40 ### ### 9 ### 40 ### ### 10 ### 40 ### ### 11 ### 40 ### ### 12 ### 40 ### ### 13 ### 40 ### ### 14 ### 40 ### ### 15 ### 40 ### ### 16 ### 40 ### ### radius Point # Section 1 radius Point # radius Point # radius Point # ### Angle 00 1 ### 2 ### 3 ### 4 ### 5 ### 6 ### 7 ### 8 ### 9 ### 10 ### 11 ### 12 ### 13 ### 14 ### 15 ### 16 ### ### Angle 00 1 ### 2 ### 3 ### 4 ### 5 ### 6 ### 7 ### 8 ### 9 ### 10 ### 11 ### 12 ### 13 ### 14 ### 15 ### 16 ### ### Angle 00 1 ### 2 ### 3 ### 4 ### 42 42 42 42 42 42 42 42 42 42 42 42 42 42 42 42 42 3.5 4.27 4.91 5.35 5.5 5.35 4.91 4.27 3.5 2.73 2.09 1.65 1.5 1.65 2.09 2.73 3.5 2.5 2.31 1.77 0.96 0 ­0.96 ­1.77 ­2.31 ­2.5 ­2.31 ­1.77 ­0.96 0 0.96 1.77 2.31 2.5 Section 2 45 45 45 45 45 45 45 45 45 45 45 45 45 45 45 45 45 3.5 4.36 5.09 5.58 5.75 5.58 5.09 4.36 3.5 2.64 1.91 1.42 1.25 1.42 1.91 2.64 3.5 2.5 2.31 1.77 0.96 0 ­0.96 ­1.77 ­2.31 ­2.5 ­2.31 ­1.77 ­0.96 0 0.96 1.77 2.31 2.5 Section 3 49 49 49 49 49 ### ### ### ### ### ### ### ### ### ### ection 4 5 ### 6 ### 7 ### 8 ### 9 ### 10 ### 11 ### 12 ### 13 ### 14 ### 15 ### 16 ### 49 49 49 49 49 49 49 49 49 49 49 49 ### ### ### ### ### ### ### ### ### ### ### ### ### ### ### ### ### ### ### ### ### ### ### ### Section 4 s 2 4 0 47 3.5 7.5 2.09 total r ctor 0 49 0 0 ### total 4 1 wetted area interference factor Skin Friction Coefficient Reynolds Number Coefficient Parasite Drag Fuselage 1.17 922.6 1 9.23E+07 0.002152 #NUM! Wing #NUM! #NUM! 1 #NUM! #NUM! #NUM! Canard #NUM! 0 1 #DIV/0! 0.000000 0.000000 Yehudi #NUM! 61.2 1 ### 0.003700 #NUM! Horizontal Tail #NUM! 204 1 8.09E+06 0.003108 #NUM! Vertical Tail #NUM! 204 1 1.28E+07 0.002888 #NUM! Nacelles 1.16 0 1 1.63E+07 0.002781 #NUM! 1.16 total #NUM! 1 Flight Conditions Atmosphere V 710.95 Viscosity 2.51E­07 h 45000 Re/l 1.81E+06 rho 0q 161.31 a 888.69 Coefficient of Lift Coefficient of Induced Drag Sum of CD Drag t/c MDD Mcr L/D Cd Cdi #NUM! #NUM! #NUM! #NUM! lb #NUM! #NUM! #NUM! #NUM! Cd0 Cl 1.22 1.22 1.21 1.2 1.18 1.17 1.2 1.19 1.22 1.2 0.18 ­0.45 ­0.4 ­0.38 Cdp form factor Drag ### 0.56 0.02 0 45 50 55 30 35 40 45 50 0 0 0 0 0 0 0 0 0 0 0 0.02 0.02 0.02 0.02 0.02 0.02 0.02 0.02 0.02 0.02 0.02 2 4 z­top z­bottom 7.5 7.5 8.54 6.46 6 8 10 0.02 0.03 0.04 0.05 Cdp­to 0.06 0.05 0.06 0.05 0.06 0.05 0.06 0.05 0.06 0.05 0.06 0.05 0.06 0.05 0.06 0.05 0.06 0.05 0.06 0.05 0.06 0.05 Cl­to 0.18 0.23 1.03 ­0.4 1.2 ­0.35 1.22 ­0.33 9.5 5.5 9.75 5.25 8.54 6.46 7.5 7.5 ­7.5 ­7.5 ­8.54 ­6.46 ­9.5 ­5.5 ­9.75 ­5.25 ­8.54 ­6.46 ­7.5 ­7.5 Drag Polar 0.06 0.07 0.08 0.09 0.1 0.11 0.12 ­0.4 ­0.42 ­0.58 ­0.75 ­0.78 ­0.79 ­0.8 1.19 1.2 1.17 1.18 1.2 1.21 1.22 ­0.35 ­0.37 ­0.53 ­0.7 ­0.73 ­0.74 ­0.75 neg­z ­8.54 ­8.47 ­8.24 ­7.9 ­7.5 ­7.1 ­6.76 ­6.53 ­6.46 ­6.53 ­6.76 ­7.1 ­7.5 ­7.9 ­8.24 ­8.47 ­8.54 ­9.5 ­9.35 ­8.91 ­8.27 ­7.5 ­6.73 0.06 ­6.09 Coefficient of Drag ­5.65 ­5.5 ­5.65 ­6.09 ­6.73 0.08 0.1 0.12 0.14 ­7.5 ­8.27 ­8.91 ­9.35 ­9.5 ­9.75 ­9.58 ­9.09 ­8.36 ­7.5 ­6.64 ­5.91 ­5.42 ­5.25 ­5.42 ­5.91 ­6.64 ­7.5 ­8.36 ­9.09 ­9.58 ­9.75 ­8.54 ­8.47 ­8.24 ­7.9 ­7.5 ­7.1 ­6.76 ­6.53 ­6.46 ­6.53 ­6.76 ­7.1 ­7.5 ­7.9 ­8.24 ­8.47 ­8.54 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 z­top z­bottom 0 0 ### ### 2.5 ­2.5 2.5 ­2.5 ### ### 0 0 z­position Parasite Drag 375.879198 #NUM! 0.000000 #NUM! #NUM! #NUM! 0.000000 #NUM! Cdp­land Cd­to Cd­land 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 Cl­land 0.23 0.23 0.23 1.08 ­0.4 1.08 1.25 ­0.35 1.25 1.27 ­0.33 1.27 1.24 1.25 1.22 1.23 1.25 1.26 1.27 ­0.35 ­0.37 ­0.53 ­0.7 ­0.73 ­0.74 ­0.75 1.24 1.25 1.22 1.23 1.25 1.26 1.27 Column AE Column AF Column AG Column AH Column AI Column AJ 0.14 Top of climb (1g steady, level flight, M = 0.80 @ h=45K, service ceiling) ρ α β M V CD0 AR e K CDC q n dh/dt g dV/dt 0 sl/ft^3 0.19 0.9496 0.8 774.48 ft/s 0.02 7.8 0.8 0.05 0 137.66 lb/ft^2 1 1.67 ft/s 32.17 ft/s^2 0 ft/s^2 ρ α Subsonic 2g manuever, 250kts @ h =10K 0 sl/ft^3 0.74 0.95 422 ft/s 0.02 7.8 0.8 156.36 lb/ft^2 2 0 ft/s 32.17 ft/s^2 0 ft/s^2 Second segment climb Takeoff ground roll 4000 ft @ Landing ground roll 2500 ft @ gradient above h = 5K, +15° h = 5K, +15° hot day h = 5K, +15° hot day hot day rho alpha beta CL max TO g s_to 0 sl/ft^3 0.84 1 1.6 32.17 ft/s^2 4000 ft rho alpha 0 sl/ft^3 0.95 rho alpha beta CL max TO g N CGR CD0 AR e_TO D CD0 β V CD0 AR e q n dh/dt g dV/dt 0.4 alpha_rev beta 1 1.6 CL max land g 32.17 ft/s^2 mu 0.3 2600 ft s_l 1 0.9 0.8 0.7 0.6 0.5 0.4 0.3 0.2 0.1 0 50 W0/S 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 Top of climb (1g steady, level flight, M = 0.80 @ h=45K, service ceiling) Subsonic 2g manuever, 250kts @ h =10K Takeoff ground roll 4000 ft @ h = 5K, +15° hot day Landing ground roll 2500 ft @ h = 5K, +15° hot day Second segment climb gradient above h = 5K, +15° hot day 0.36 60 70 80 90 100 110 120 130 140 150 W0/S 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 TSL/W0 CL check W0/S 0.14 0.61 0.14 0.62 0.14 0.63 0.14 0.64 0.14 0.66 0.14 0.67 0.15 0.68 0.15 0.69 0.15 0.7 0.15 0.72 0.15 0.73 0.15 0.74 0.15 0.75 0.15 0.77 0.15 0.78 0.15 0.79 0.15 0.8 0.15 0.81 0.15 0.83 0.16 0.84 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 TSL/W0 0.18 0.18 0.18 0.19 0.19 0.19 0.2 0.2 0.2 0.21 0.21 0.22 0.22 0.22 0.23 0.23 0.23 0.24 0.24 0.24 W0/S 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 TSL/W0 ­0.21 ­0.2 ­0.19 ­0.18 ­0.17 ­0.16 ­0.14 ­0.13 ­0.12 ­0.11 ­0.1 ­0.09 ­0.08 ­0.06 ­0.05 ­0.04 ­0.03 ­0.02 ­0.01 0 W0/S 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 TSL/W0 0.34 0.34 0.33 0.33 0.33 0.33 0.32 0.32 0.32 0.32 0.32 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.3 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.32 0.32 0.32 0.32 0.32 0.32 0.32 0.32 0.32 0.32 0.32 0.33 0.33 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 0.16 0.16 0.16 0.16 0.16 0.16 0.16 0.16 0.16 0.17 0.17 0.17 0.17 0.17 0.17 0.17 0.17 0.17 0.18 0.18 0.18 0.18 0.18 0.18 0.18 0.18 0.19 0.19 0.19 0.19 0.19 0.19 0.19 0.19 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.21 0.21 0.21 0.21 0.21 0.21 0.21 0.22 0.22 0.22 0.22 0.22 0.22 0.22 0.23 0.23 0.23 0.23 0.85 0.86 0.87 0.89 0.9 0.91 0.92 0.94 0.95 0.96 0.97 0.98 1 1.01 1.02 1.03 1.05 1.06 1.07 1.08 1.09 1.11 1.12 1.13 1.14 1.15 1.17 1.18 1.19 1.2 1.22 1.23 1.24 1.25 1.26 1.28 1.29 1.3 1.31 1.32 1.34 1.35 1.36 1.37 1.39 1.4 1.41 1.42 1.43 1.45 1.46 1.47 1.48 1.49 1.51 1.52 1.53 1.54 1.56 1.57 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 0.25 0.25 0.25 0.26 0.26 0.26 0.27 0.27 0.28 0.28 0.28 0.29 0.29 0.29 0.3 0.3 0.3 0.31 0.31 0.31 0.32 0.32 0.32 0.33 0.33 0.34 0.34 0.34 0.35 0.35 0.35 0.36 0.36 0.36 0.37 0.37 0.37 0.38 0.38 0.38 0.39 0.39 0.4 0.4 0.4 0.41 0.41 0.41 0.42 0.42 0.42 0.43 0.43 0.43 0.44 0.44 0.44 0.45 0.45 0.46 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 0.02 0.03 0.04 0.05 0.06 0.07 0.08 0.1 0.11 0.12 0.13 0.14 0.15 0.16 0.18 0.19 0.2 0.21 0.22 0.23 0.25 0.26 0.27 0.28 0.29 0.3 0.31 0.33 0.34 0.35 0.36 0.37 0.38 0.39 0.41 0.42 0.43 0.44 0.45 0.46 0.47 0.49 0.5 0.51 0.52 0.53 0.54 0.55 0.57 0.58 0.59 0.6 0.61 0.62 0.63 0.65 0.66 0.67 0.68 0.69 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 0.33 0.33 0.33 0.33 0.33 0.33 0.33 0.34 0.34 0.34 0.34 0.34 0.34 0.34 0.34 0.34 0.35 0.35 0.35 0.35 0.35 12 0.2 0.19 0.19 0.19 0.18 0.18 0.18 0.17 0.17 0.17 0.17 0.17 0.16 0.16 0.16 0.16 0.15 0.15 0.15 0.15 0.15 0.15 0.14 0.14 0.14 0.14 0.14 0.14 0.14 0.13 0.13 0.13 0.13 0.13 0.13 0.13 0.13 0.12 13 0.27 0.28 0.3 0.31 0.33 0.34 0.36 0.37 0.39 0.4 0.41 0.43 0.44 0.45 0.47 0.48 0.49 0.51 0.52 0.53 0.55 0.56 0.57 0.59 0.6 0.61 0.62 0.64 0.65 0.66 0.67 0.68 0.7 0.71 0.72 0.73 0.75 0.76 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 14 49.66 50.66 51.67 52.67 53.67 54.67 55.68 56.68 57.68 58.68 59.68 60.69 61.69 62.69 63.69 64.69 65.69 66.69 67.69 68.7 69.7 70.7 71.7 72.7 73.7 74.7 75.7 76.7 77.7 78.7 79.7 80.7 81.7 82.7 83.7 84.7 85.7 86.7 0.23 0.23 0.23 0.24 0.24 0.24 0.24 0.24 0.24 0.24 0.25 0.25 0.25 0.25 0.25 0.25 0.25 0.26 0.26 0.26 0.26 15 0.16 0.16 0.15 0.14 0.14 0.13 0.13 0.12 0.11 0.11 0.1 0.1 0.09 0.09 0.08 0.08 0.07 0.07 0.07 0.06 0.06 0.05 0.05 0.04 0.04 0.04 0.03 0.03 0.02 0.02 0.02 0.01 0.01 0.01 0 0 0 0.01 1.58 1.59 1.6 1.62 1.63 1.64 1.65 1.66 1.68 1.69 1.7 1.71 1.73 1.74 1.75 1.76 1.77 1.79 1.8 1.81 1.82 23 0.03 0.04 0.04 0.04 0.05 0.05 0.05 0.05 0.06 0.06 0.06 0.07 0.07 0.07 0.07 0.08 0.08 0.08 0.09 0.09 0.09 0.09 0.1 0.1 0.1 0.1 0.11 0.11 0.11 0.11 0.12 0.12 0.12 0.12 0.13 0.13 0.13 0.13 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 24 0.36 0.34 0.33 0.32 0.31 0.3 0.29 0.28 0.27 0.26 0.25 0.24 0.23 0.21 0.2 0.19 0.18 0.17 0.16 0.15 0.14 0.13 0.12 0.11 0.1 0.09 0.08 0.07 0.06 0.05 0.04 0.03 0.02 0.01 0.01 0.02 0.03 0.04 0.46 0.46 0.47 0.47 0.47 0.48 0.48 0.48 0.49 0.49 0.49 0.5 0.5 0.5 0.51 0.51 0.52 0.52 0.52 0.53 0.53 25 0.17 0.17 0.17 0.17 0.17 0.17 0.17 0.16 0.16 0.16 0.16 0.16 0.16 0.16 0.16 0.16 0.16 0.16 0.16 0.16 0.15 0.15 0.15 0.15 0.15 0.15 0.15 0.15 0.15 0.15 0.14 0.14 0.14 0.14 0.14 0.14 0.14 0.14 34 0.39 0.38 0.37 0.37 0.36 0.35 0.34 0.33 0.33 0.32 0.31 0.3 0.29 0.29 0.28 0.27 0.26 0.25 0.25 0.24 0.23 0.22 0.22 0.21 0.2 0.19 0.18 0.18 0.17 0.16 0.15 0.14 0.14 0.13 0.12 0.11 0.1 0.1 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 35 0.13 0.13 0.13 0.12 0.12 0.12 0.11 0.11 0.11 0.1 0.1 0.1 0.09 0.09 0.09 0.08 0.08 0.07 0.07 0.07 0.06 0.06 0.06 0.05 0.05 0.05 0.04 0.04 0.04 0.03 0.03 0.03 0.02 0.02 0.01 0.01 0.01 0 0.7 0.72 0.73 0.74 0.75 0.76 0.77 0.78 0.8 0.81 0.82 0.83 0.84 0.85 0.86 0.88 0.89 0.9 0.91 0.92 0.93 45 0.52 0.51 0.5 0.49 0.48 0.47 0.46 0.44 0.43 0.42 0.41 0.4 0.39 0.38 0.36 0.35 0.34 0.33 0.32 0.31 0.3 0.28 0.27 0.26 0.25 0.24 0.23 0.21 0.2 0.19 0.18 0.17 0.16 0.15 0.13 0.12 0.11 0.1 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 Max 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 0.12 0.12 0.12 0.12 0.12 0.12 0.12 0.12 0.12 0.12 0.11 0.11 0.11 0.11 0.11 0.11 0.11 0.11 0.11 0.11 0.11 0.11 0.11 0.11 0.11 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.09 0.09 0.09 0.09 0.09 0.09 0.09 0.09 0.09 0.09 0.09 0.09 0.09 0.77 0.78 0.79 0.81 0.82 0.83 0.84 0.85 0.86 0.88 0.89 0.9 0.91 0.92 0.93 0.95 0.96 0.97 0.98 0.99 1 1.02 1.03 1.04 1.05 1.06 1.07 1.08 1.09 1.11 1.12 1.13 1.14 1.15 1.16 1.17 1.18 1.2 1.21 1.22 1.23 1.24 1.25 1.26 1.27 1.29 1.3 1.31 1.32 1.33 1.34 1.35 1.36 1.37 1.38 1.4 1.41 1.42 1.43 1.44 87.7 88.7 89.7 90.7 91.7 92.7 93.7 94.7 95.7 96.7 97.7 98.7 99.7 100.7 101.69 102.69 103.69 104.69 105.69 106.69 107.69 108.69 109.69 110.69 111.69 112.69 113.69 114.69 115.69 116.68 117.68 118.68 119.68 120.68 121.68 122.68 123.68 124.68 125.68 126.68 127.67 128.67 129.67 130.67 131.67 132.67 133.67 134.67 135.67 136.66 137.66 138.66 139.66 140.66 141.66 142.66 143.66 144.66 145.65 146.65 0.01 0.01 0.02 0.02 0.02 0.03 0.03 0.03 0.04 0.04 0.04 0.05 0.05 0.05 0.05 0.06 0.06 0.06 0.07 0.07 0.07 0.08 0.08 0.08 0.08 0.09 0.09 0.09 0.09 0.1 0.1 0.1 0.11 0.11 0.11 0.11 0.12 0.12 0.12 0.12 0.13 0.13 0.13 0.13 0.14 0.14 0.14 0.14 0.15 0.15 0.15 0.15 0.16 0.16 0.16 0.16 0.17 0.17 0.17 0.17 0.13 0.14 0.14 0.14 0.14 0.15 0.15 0.15 0.15 0.16 0.16 0.16 0.16 0.16 0.17 0.17 0.17 0.17 0.18 0.18 0.18 0.18 0.18 0.19 0.19 0.19 0.19 0.2 0.2 0.2 0.2 0.2 0.21 0.21 0.21 0.21 0.21 0.22 0.22 0.22 0.22 0.23 0.23 0.23 0.23 0.23 0.24 0.24 0.24 0.24 0.24 0.25 0.25 0.25 0.25 0.26 0.26 0.26 0.26 0.26 0.05 0.06 0.07 0.08 0.09 0.1 0.11 0.12 0.13 0.14 0.15 0.16 0.17 0.18 0.19 0.2 0.21 0.22 0.23 0.24 0.25 0.26 0.27 0.28 0.29 0.3 0.31 0.32 0.33 0.34 0.35 0.36 0.37 0.38 0.39 0.4 0.41 0.42 0.43 0.44 0.45 0.46 0.47 0.48 0.49 0.5 0.51 0.52 0.53 0.54 0.55 0.56 0.57 0.58 0.59 0.6 0.61 0.62 0.63 0.64 0.14 0.13 0.13 0.13 0.13 0.13 0.13 0.13 0.13 0.12 0.12 0.12 0.12 0.12 0.12 0.12 0.12 0.11 0.11 0.11 0.11 0.11 0.11 0.11 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.09 0.09 0.09 0.09 0.09 0.09 0.09 0.08 0.08 0.08 0.08 0.08 0.08 0.08 0.07 0.07 0.07 0.07 0.07 0.07 0.07 0.06 0.06 0.06 0.06 0.06 0.06 0.06 0.09 0.08 0.07 0.06 0.06 0.05 0.04 0.03 0.02 0.02 0.01 0 0.01 0.02 0.02 0.03 0.04 0.05 0.05 0.06 0.07 0.08 0.09 0.09 0.1 0.11 0.12 0.13 0.13 0.14 0.15 0.16 0.17 0.17 0.18 0.19 0.2 0.21 0.21 0.22 0.23 0.24 0.25 0.25 0.26 0.27 0.28 0.28 0.29 0.3 0.31 0.32 0.32 0.33 0.34 0.35 0.36 0.36 0.37 0.38 0 0 0.01 0.01 0.01 0.02 0.02 0.02 0.03 0.03 0.03 0.04 0.04 0.05 0.05 0.05 0.06 0.06 0.06 0.07 0.07 0.07 0.08 0.08 0.08 0.09 0.09 0.09 0.1 0.1 0.11 0.11 0.11 0.12 0.12 0.12 0.13 0.13 0.13 0.14 0.14 0.14 0.15 0.15 0.15 0.16 0.16 0.17 0.17 0.17 0.18 0.18 0.18 0.19 0.19 0.19 0.2 0.2 0.2 0.21 0.09 0.08 0.07 0.05 0.04 0.03 0.02 0.01 0 0.01 0.03 0.04 0.05 0.06 0.07 0.08 0.09 0.11 0.12 0.13 0.14 0.15 0.16 0.17 0.19 0.2 0.21 0.22 0.23 0.24 0.26 0.27 0.28 0.29 0.3 0.31 0.32 0.34 0.35 0.36 0.37 0.38 0.39 0.4 0.42 0.43 0.44 0.45 0.46 0.47 0.48 0.5 0.51 0.52 0.53 0.54 0.55 0.56 0.58 0.59 88 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 min 0.09 0.09 0.09 0 1.45 1.46 1.47 0 147.65 148.65 149.65 0 0.17 0.18 0.18 0 0.27 0.27 0.27 0 0.65 0.66 0.67 0.01 0.05 0.05 0.05 0 0.39 0.4 0.4 0 0.21 0.21 0.22 0 0.6 0.61 0.62 0 148 149 150 Max max2 First Point x y Second segment climb gradient above h = 5K, +15° hot day 0 0.84 1 1.5 32.17 ft/s^2 2 2.4 % 0 7.8 0.6 0 W0/S TSL/W0 W0/S & TSL/W0 Value Average Fudge Factor Included 97.5 W0/S 0.33 TSL/W0 92.63 0.36 Landing ground roll 2500 ft @ h = 5K, +15° hot day Second segment climb gradient above h = 5K, +15° hot day 0.36 TSL/W0 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 y 5000 ft rho = p= R= T= 0 sl/ft3 1760.9 lb/ft2 1718 ft-lb/sl-ºR 500.86 ºR 5000 ft hot day (∆T = +15) 0 sl/ft3 1760.9 lb/ft2 1718 ft-lb/sl-ºR 515.86 ºR 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 12 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 13 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 14 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 15 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0.3 0 0 23 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 24 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0.17 0 0 0 0 25 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 34 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 35 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 45 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 12 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 13 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0.35 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0.31 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0.31 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0.3 0.3 0 0 0 0 0 0 0 0 0.17 0.17 0 0 0 0 0 0 0 0 0.35 0 0 0 0 0.31 0.31 0 0 0 0.31 y 0.31 x x2 0 0 0 0 0 0 0 0 0 0 0 0 First Point 99 0.35 Second Point 96 0.31 Average x y 97.5 0.33 Fudge Factor Included 92.63 0.36 14 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 15 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 85 0 0 23 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 24 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 83 0 0 0 0 25 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 34 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 35 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 45 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 99 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 88 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 96 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 85 0 0 0 0 0 0 0 0 0 0 0 83 0 0 0 0 0 0 0 0 0 0 0 99 99 0 0 0 0 88 0 88 0 0 0 96 0 96 Outer Structure W0 guess #NUM! lb number of passengers 9 number of flight crew 2 We/W0 #NUM! empty weight fraction Wpayload 2160 lb Wcrew 480 lb W0 design #NUM! lb We design #NUM! lb Wf design #NUM! lb design mission range 3700 nmi alternate airport range 200 nmi reserve loiter 0.6 hr AR 7.8 T/W0 0.36 W0/S 92.63 lb/ft2 Mmax 0.820 subsonic (L/D)max 18.02 subsonic (L/D)cruise 15.68 subsonic (L/D)loiter 18.02 SFCcruise 0.5 1/hr Mcruise 0.800 Vcruise @ 42,000 ft 458.54 kts SFCloiter 0.4 1/hr design mission W1/W0 0.97 takeoff W2/W1 0.98 climb W3/W2 0.77310 cruise W4/W3 1 land W5/W4 0.97 missed approach (TO) W6/W5 0.98 climb W7/W6 0.98619 divert to alternate W8/W7 0.98677 hold W9/W8 1 land W9/W0 0.67169 Wf/W0 0.33160 fuel weight fraction Thrust #NUM! S #NUM! Initial Weight Prediction X­ # Location 1 #NUM! 1 40.72 1 39.81 1 44.5 1 #NUM! 1 11 1 43 1 43 1 43 1 #NUM! 1 11 1 43 1 11 1 #NUM! 1 #NUM! 1 7.33 2 #NUM! 2 40.72 2 #NUM! 2 #NUM! 1 44.5 1 43 2 #NUM! 1 20 1 16.7 Seat2 1 17.7 Seat3 1 25.46 Seat4 1 30.34 Seat5 1 15.63 Seat6 1 30.34 Sofa 1 21.65 Laboratory 1 33.9 Gally 1 13 Environmental Control 20 1 APU 1 43 Pilot 2 20 Passanger1 1 16.7 Passanger2 1 17.7 Passanger3 1 25.46 Passanger4 1 30.34 Passanger5 1 15.63 Passanger6 1 30.34 Name Wwing Whorizont Wverticalt altail Wfuselag ail Wmain e Wnose landing landing gear Wnacelle gear Wengine group Wstarter( controls pneumati Wfuel c) Wflight system Wapu controls Winstrum installed Wfurnishi Whydrauli ents ng(does Welectric cs not al Wavionics include Waircondi cargo tioning handling Wanti­ice Whandlin gear or g gear seats) Wcargo Wengine handling gear and Avionics seats Seat1 Center of Gravity Weight #NUM! #NUM! 0 0 798.17 214.15 0 40.4 84.66 283.58 456.01 198 #NUM! #NUM! 586.26 #NUM! 269.55 #NUM! 0 0 300 ­719.43 700 234 34 34 34 34 34 34 34 34 34 30 90 234 195 195 195 195 195 195 Payload Inner Structure Passanger7 Passanger8 Passanger9 Luggage Total 0 Payload 1 1 1 2 21.65 21.65 21.65 #NUM! #NUM! 195 195 195 234 #NUM! vity Moment From Zero #NUM! Point #NUM! 0 0 #NUM! 2355.66 0 1737.2 3640.3 #NUM! 5016.16 8514 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! ­ 13350 30935.4 #NUM! 9 4680 567.8 601.8 865.64 1031.39 531.42 1031.39 736.1 1152.6 442 600 3870 4680 3256.5 3451.5 4964.7 5915.33 3047.85 5915.33 Constants Constants A Bh Bw D De Fw Ht Ht/Hv Hv Iy Kcb Kdoor Kdw Kdwf Kh KLg Kmc Kmp Kng Knp Kp Kr Krht Ktp Ktpg Ktr Kuht Kvg Kvs Kvsh Kws Ky Kz L La Ld Lec Lf Lm Ln Lt Ltp Value Option 7.8 aspect ratio 22.36 horizontal tail span #NUM! wingspan 1.5 fuselage structural depth 2.09 engine diameter 7 fuselage width at horizontal tail intersection ft 3.5 horizontal tail height above fuselage ft 0 0 for conventional tail, 1 for "T" tail 4.27 vertical tail height above fuselage 2500 yawing moment of inertia lb­ft^2 1 2.25 for cross­beam gear, 1 otherwise 1 1 for no cargo door, 1.06 for on side cargo door, 1. 1 0.768 for delta wing 1 otherwise 1 0.774 for deltawing aircraft 1 otherwise 0.12 0.05 for low subsonic flight 0.11 for midium subsonic flight, 0.12 for high subso 1.12 1.12 for fuselage mounted 1 otherwise 1.45 1.45 if mission completiong required after failure 1 otherwise 1 1.126 for kneeling gear 1 otherwise 1.02 1.017 for pylon mounted nacelle 1 otherwise 1 1.15 for kneeling gear 1 otherwise 1 1.4 for engine with propeller 1 otherwise 1 1.133 if reciprocating engine 1 otherwise 1.05 1.047 for rolling horizontal tail otherwise 1 0.79 0.793 if turboprop 1 otherwise 1 0.826 for tripod gear 1 otherwise 1.18 1.18 for jet with thrust reversals 1 otherwise 1 1.143 for unit(all­moving) horizontal tail 1 otherwise 1 1.62 for variable geometry 1 otherwise 1 1.19 for variable sweep wing 1 otherwise 1 1.425 for variable sweep wing 1 otherwise 4.32 aircraft pitching radius of gyration (~=0.3Lt) 14.4 aircraft yawing radius of gyration (~=Lt) 48 Fuselage structural length(excludes radome cowling, tail cap) 38 Electrical routing distance(generators to avionics to cockpit) 2 Duct Length 38 length from engine front to cockpit 51 total fuselage length 60 extended length of main landing gear in 60 extended nose gear length in 14.4 tail length; wing quarter 1 length of tail pipe 4221.75 4221.75 4221.75 #NUM! #NUM! M Nc Nci Nen Nf Ngen NLt Nl Nm Nmss Nmw Nnw Np Nt Nu Nw Nz Rkva Scs Scsw Se Sf Sht Sn Svt Sw SFC Vi Vp Vpr Vt Wc Wdg Wec Wen Wl Wuav Lamda lamda t/c Fw/Bh Lamdaht Ah Lamdavt Av 0.800 mach number 2 number of crew 2 number of crew equivalents 2 number of engines 5 number of functions performed by controls (4~7) 2 number of generators(typically Nen) 9 nacelle length ft 3 ultimate landing load factor ;=Ngear*1.5 1 number of mechanical functions (typically 0~2) 2 number of main gear shock struts 2 number of main wheels 1 number of nose wheels 11 number of personnel onboard (crew+passengers) 5 number of fuel tanks 7 number of hydraulic utiliity functions (typically 5~15) 4.5 nacelle width ft 5 ultimate load factor ;=1.5*limit load factor 50 system electrical rating kV*A (Typically 40~50 for transports) 70 total area of control surfaces ft^2 78 control surface area ft^2 20 elevator area ft^2 922.6 fuselage wetted area ft^2 100 horizontal tail area ft^2 0 nacelle wetted area ft^2 100 vertical tail area ft^2 #NUM! trapazoidal wing area ft^2 0.5 Engine Specific fuel consumption­­maximum thrust 2180 integral tanks volume gal 0 self­sealing tanks volume gal 935 volume of pressurized section ft^3 2180 total fuel volume gal 4000 maximum cargo weight lb #NUM! flight design gross weight lb 1836 weight of engine and contents lb 1364 engine weight, each lb 25000 landing design gross weight lb #NUM! uninstalled avionics weight lb (typically 800~1400 #NUM! wing sweep at 25% MAC 0.5 taper ratio #NUM! #NUM! 21.78 horizontal tail wing sweep 100 area of horizontal tail 22.33 Vertical tail wing sweep 100 area of vertical tail t/c vertical L/D Vstall 0.5 32 88.64 Detailed Weight Prediction W0 guess W0 design Wf design We/W0 #NUM! #NUM! #NUM! #NUM! #NUM! We Thrust #NUM! Wing Area #NUM! Wwing #NUM! Whorizontaltail #NUM! Wverticaltail #NUM! Wfuselage #NUM! Wmain landing gear 798.17 Wnose landing gear 214.15 Wnacelle group 0 Wengine controls 40.4 Wstarter(pneumatic) 84.66 Wfuel system 283.58 Wflight controls 456.01 Wapu installed 198 Winstruments #NUM! Whydraulics #NUM! Welectrical 586.26 Wavionics #NUM! Wfurnishing(does not include cargo handling gear or seats) 269.55 Wairconditioning #NUM! Wanti­ice #NUM! Whandling gear #NUM! Wengine #NUM! Wcargo handling gear and seats 700 #NUM! ome cowling, tail cap) o avionics to cockpit) load factor ically 40~50 for transports) imum thrust ly 800~1400 NACA number m (maximum chamber) p (location of maximum chamber) maximum thickness 2414 0.02 0.40 0.14 t 0.14 c #NUM! m 0.02 3 2.5 2 1.5 1 0.5 0 -0.5 -1 0 Section x 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! y 2 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! yc 4 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! 6 8 10 12 xupper yupper xlower ylower #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! p 0.40 10 theta 12 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! Mission Detail Misson Distance Altitude Acculative Distance Taxi Distance h R gamma T0 P0 rho0 Th_trop Th_stra h_trop h_stra g T1 P1 P2 T P rho a Ft to Miles Hour Mach Number Velocity Flgith Time Wind AC Weight Cl Fuel FractionW1/W0 Fuel Weight 4000 173.26 #NUM! #NUM! 0.97 W2/W1 #NUM! #NUM! 107939596.0 #NUM! #DIV/0! 3346421.3 9465108.8 14965651.0 #NUM! #NUM! 230661995.4 #NUM! #DIV/0! 7151149.8 20226505.9 31980913.9 0.2 223.26 17.92 23.09 10560 596.38 #NUM! #NUM! 0.99 W3/W2 #NUM! #NUM! 101374689.0 #NUM! #DIV/0! 3142891.3 8889439.0 14055437.3 0.6 646.38 16.34 17.71 520.4 158400 #NUM! #NUM! 0.75 W4/W3 #NUM! #NUM! 92278661.8 #NUM! #DIV/0! 2860889.7 8091818.1 12794287.7 0.65 570.4 277.7 304.38 0.8 710.95 18003760 660.95 25323.48 27239.16 105600 265.96 #NUM! #NUM! 0.99 W5/W4 #NUM! #NUM! 92949033.8 #NUM! #DIV/0! 2881673.1 8150602.3 12887233.8 4000 0h 1716 R 1.4 gamma 518.69 T0 2116.2 P0 0 rho0 0 Th_trop 0 Th_stra 36152 h_trop 82346 h_stra 32.2 g 389.99 T1 470.674 P1 50.98 P2 518.69 T 2116.2 P 0 rho 1116.29 a 0.76 Miles Initial 0 0 0 Taxi 0.76 0 0.76 Take off Distance 2 10000 h 1716 R 1.4 gamma 518.69 T0 2116.2 P0 0 rho0 0 Th_trop 0 Th_stra 36152 h_trop 82346 h_stra 32.2 g 389.99 T1 470.674 P1 50.98 P2 483.09 T 1454.76 P 0 rho 1077.3 a 2 Miles Takeoff 2 10000 2.76 Climb 30 40000 32.76 Climb Distance 30 40000 h 1716 R 1.4 gamma 518.69 T0 2116.2 P0 0 rho0 0 Th_trop 0 Th_stra 36152 h_trop 82346 h_stra 32.2 g 389.99 T1 470.674 P1 50.98 P2 320.54 T 480.74 P 0 rho 877.54 a 30 Miles Cruise 3409.8 45000 3442.56 Loiter Attept to Land 20 16000 3462.56 Cruise Distance 3409.8 45000 h 1716 R 1.4 gamma 518.69 T0 2116.2 P0 0 rho0 0 Th_trop 0 Th_stra 36152 h_trop 82346 h_stra 32.2 g 389.99 T1 470.674 P1 50.98 P2 328.74 T 360.07 P 0 rho 888.69 a 3409.8 Miles 0.5 0.3 315.96 0.95 2000 3463.51 Climb 16 10000 3479.51 Loiter Distance #NUM! #NUM! Total Weight Fuselage Wing Canard Yehudi Horizontal Tail Vertical Tail Reynold's Nacelles Fuselage Wing Canard Yehudi Horizontal Tail Vertical Tail Nacelles 19048164.0 0.00210572 #NUM! #DIV/0! 0.00360135 0.00303031 0.00281823 0.00271478 40705058.0 0.00189811 #NUM! #DIV/0! 0.00317113 0.00268986 0.00250971 0.00242154 #NUM! #NUM! 0.00000000 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! 17889651.0 0.00212427 #NUM! #DIV/0! 0.00364045 0.00306106 0.00284603 0.00274118 #NUM! #NUM! 0.00000000 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! 16284469.7 0.00215247 #NUM! #DIV/0! 0.00370014 0.00310796 0.00288841 0.00278140 #NUM! #NUM! 0.00000000 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! 16402770.7 0.00215028 #NUM! #DIV/0! 0.00369550 0.00310431 0.00288511 0.00277827 #NUM! #NUM! 0.00000000 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! Skin Friction Fuselage #NUM! Wing #NUM! Canard 0.00000000 Yehudi #NUM! Horizontal Tail #NUM! Vertical Tail #NUM! Nacelles #NUM! Total CD Parasite #NUM! Induced Drag Total CD Drag 50000 40000 30000 20000 10000 0 -10000 0 -500 -100 -200 -300 -400 -500 -600 -500 0 0 #NUM! #NUM! #NUM! Coefficient of P 500 1000 1500 2 500 1000 1500 20 Name Err:509 Err:509 Err:509 X­Location #NUM! 40.72 39.81 Weight #NUM! #NUM! 0 Take Off Gear up Fuselage Tank Wing Tank Moment Moment Moment From Zero Weight From Zero Weight From Zero Weight #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! Point Point Point #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! 0 0 0 0 0 0 Err:509 44.5 0 Err:509 #NUM! 798.17 Err:509 11 214.15 Err:509 43 0 Err:509 43 40.4 Err:509 43 84.66 Err:509 #NUM! 283.58 Err:509 11 456.01 Err:509 43 198 Err:509 11 #NUM! Err:509 #NUM! #NUM! Err:509 #NUM! 586.26 Err:509 7.33 #NUM! Err:509 #NUM! 269.55 Err:509 40.72 #NUM! Err:509 #NUM! 0 Err:509 #NUM! 0 Err:509 43 ­719.43 Err:509 #NUM! 700 Avionics 20 234 Seat1 16.7 34 Seat2 17.7 34 Seat3 25.46 34 Seat4 30.34 34 Seat5 15.63 34 Seat6 30.34 34 Sofa 21.65 34 Laboratory 33.9 34 Gally 13 34 Environmental Control 20 30 APU 43 90 Fuel Pilot Passanger1 Passanger2 Passanger3 Passanger4 Passanger5 Passanger6 Passanger7 Passanger8 Passanger9 Luggage 0 Take Off 20 16.7 17.7 25.46 30.34 15.63 30.34 21.65 21.65 21.65 #NUM! #NUM! #NUM! Gear up #NUM! 234 195 195 195 195 195 195 195 195 195 234 #NUM! 0 0 #NUM! 798.17 2355.66 214.15 0 0 1737.2 40.4 3640.3 84.66 #NUM! 283.58 5016.16 456.01 8514 198 #NUM! #NUM! #NUM! #NUM! #NUM! 586.26 #NUM! #NUM! #NUM! 269.55 #NUM! #NUM! #NUM! 0 #NUM! 0 ­30935.49 ­719.43 #NUM! 700 4680 234 567.8 34 601.8 34 865.64 34 1031.39 34 531.42 34 1031.39 34 736.1 34 1152.6 34 442 34 600 30 3870 90 #NUM! 3907.8 3451.5 4964.7 5915.33 3047.85 5915.33 4221.75 4221.75 4221.75 #NUM! #NUM! #NUM! #NUM! 234 195 195 195 195 195 195 195 195 195 234 #NUM! 0 #NUM! 2355.66 0 1737.2 3640.3 #NUM! 5016.16 8514 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! ­30935.49 #NUM! 4680 567.8 601.8 865.64 1031.39 531.42 1031.39 736.1 1152.6 442 600 3870 #NUM! 3907.8 3451.5 4964.7 5915.33 3047.85 5915.33 4221.75 4221.75 4221.75 #NUM! #NUM! #NUM! 0 798.17 214.15 0 40.4 84.66 283.58 456.01 198 #NUM! #NUM! 586.26 #NUM! 269.55 #NUM! 0 0 ­719.43 700 234 34 34 34 34 34 34 34 34 34 30 90 #NUM! 234 195 195 195 195 195 195 195 195 195 234 #NUM! 0 #NUM! 2355.66 0 1737.2 3640.3 #NUM! 5016.16 8514 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! ­30935.49 #NUM! 4680 567.8 601.8 865.64 1031.39 531.42 1031.39 736.1 1152.6 442 600 3870 #NUM! 3907.8 3451.5 4964.7 5915.33 3047.85 5915.33 4221.75 4221.75 4221.75 #NUM! #NUM! #NUM! 0 798.17 214.15 0 40.4 84.66 283.58 456.01 198 #NUM! #NUM! 586.26 #NUM! 269.55 #NUM! 0 0 ­719.43 700 234 34 34 34 34 34 34 34 34 34 30 90 #NUM! 234 195 195 195 195 195 195 195 195 195 234 #NUM! Total Payload Fuel Inner Structure Outer Structure Fuselage Tank Wing Tank Gear DownLand Reserve Fuel Passenger Off Crew Off CG Weight #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! Divert 200 40000 3679.51 Loiter 20 16000 h 1716 R Loiter 20 16000 3699.51 Distance Land 0.49 2000 3700 Climb Distance 16 10000 h 1716 R 1.4 gamma 518.69 T0 2116.2 P0 0 rho0 0 Th_trop 0 Th_stra 36152 h_trop 82346 h_stra 32.2 g 389.99 T1 470.674 P1 50.98 P2 483.09 T 1454.76 P 0 rho 1077.3 a 16 Miles 0.65 700.25 9.02 9.91 84480 650.25 120.64 129.92 1056000 652.03 0.8 702.03 1504.21 1619.56 105600 265.96 Divert Distance 200 40000 h 1716 R 1.4 gamma 518.69 T0 2116.2 P0 0 rho0 0 Th_trop 0 Th_stra 36152 h_trop 82346 h_stra 32.2 g 389.99 T1 470.674 P1 50.98 P2 320.54 T 480.74 P 0 rho 877.54 a 200 Miles 0.3 0.3 315.96 334.22 397.05 2600 227.15 #NUM! #NUM! 1 W9/W0 #NUM! #NUM! 92949033.8 #NUM! #DIV/0! 2881673.1 8150602.3 12887233.8 #NUM! #NUM! 126314070.8 #NUM! #DIV/0! 3916080.0 11076347.0 17513242.4 Loiter Distance 20 16000 h 1716 R 1.4 gamma 518.69 T0 2116.2 P0 0 rho0 0 Th_trop 0 Th_stra 36152 h_trop 82346 h_stra 32.2 g 389.99 T1 470.674 P1 50.98 P2 461.73 T 1146.22 P 0 rho 1053.21 a 20 Ft to Miles 0.25 277.15 Land Distance 5000 2000 h 1716 R 1.4 gamma 518.69 T0 2116.2 P0 0 rho0 0 Th_trop 0 Th_stra 36152 h_trop 82346 h_stra 32.2 g 389.99 T1 470.674 P1 50.98 P2 511.57 T 1967.51 P 0 rho 1108.6 a 0.95 Miles Attempt to Land 1.4 gamma 518.69 T0 2116.2 P0 0 rho0 0 Th_trop 0 Th_stra 36152 h_trop 82346 h_stra 32.2 g 389.99 T1 470.674 P1 50.98 P2 461.73 T 1146.22 P 0 rho 1053.21 a 20 Ft to Miles 0.5 0.3 315.96 334.22 397.05 #NUM! #NUM! 0.97 W6/W5 #NUM! #NUM! Reynold's number 92949033.8 #NUM! #DIV/0! 2881673.1 8150602.3 12887233.8 252628141.6 #NUM! #DIV/0! 7832160.1 22152694.0 35026484.7 #NUM! #NUM! 5000 504.3 #NUM! #NUM! 0.5 554.3 #NUM! #NUM! 0.99 W7/W6 #NUM! #NUM! 249883828.3 #NUM! #DIV/0! 7747078.9 21912048.1 34645990.1 0.98 W8/W7 #NUM! #NUM! 0.99 W9/W8 #NUM! #NUM! 124768848.0 #NUM! #DIV/0! 3868173.9 10940848.1 17298999.7 #NUM! #NUM! 16402770.7 0.00215028 #NUM! #DIV/0! 0.00369550 0.00310431 0.00288511 0.00277827 #NUM! #NUM! 0.00000000 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! 44581436.8 0.00187517 #NUM! #DIV/0! 0.00312446 0.00265270 0.00247594 0.00238940 #NUM! #NUM! 0.00000000 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! 44097146.2 0.00187790 #NUM! #DIV/0! 0.00313001 0.00265712 0.00247996 0.00239323 #NUM! #NUM! 0.00000000 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! 22018032.0 0.00206376 #NUM! #DIV/0! 0.00351327 0.00296091 0.00275545 0.00265516 #NUM! #NUM! 0.00000000 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! 16402770.7 0.00215028 #NUM! #DIV/0! 0.00369550 0.00310431 0.00288511 0.00277827 #NUM! #NUM! 0.00000000 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! 22290718.4 0.00206025 #NUM! #DIV/0! 0.00350592 0.00295512 0.00275020 0.00265018 #NUM! #NUM! 0.00000000 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! Skin Friction Coefficient Coefficient of Parasite Drag 31000 29000 27000 25000 500 2000 2500 3000 3500 4000 23000 21000 19000 17000 15000 00 2000 Wing Tank Gear Down Land Reserve Fuel Passenger Off Crew Off Moment Moment Moment Moment Moment From Zero Weight From Zero Weight From Zero Weight From Zero Weight From Zero Weight #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! Point Point Point Point Point #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! 0 0 0 0 0 0 0 0 0 0 CG Travel 2500 3000 3500 4000 20 0 #NUM! 2355.66 0 1737.2 3640.3 #NUM! 5016.16 8514 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! ­30935.49 #NUM! 4680 567.8 601.8 865.64 1031.39 531.42 1031.39 736.1 1152.6 442 600 3870 #NUM! 3907.8 3451.5 4964.7 5915.33 3047.85 5915.33 4221.75 4221.75 4221.75 #NUM! #NUM! #NUM! Add Fuel 0 798.17 214.15 0 40.4 84.66 283.58 456.01 198 #NUM! #NUM! 586.26 #NUM! 269.55 #NUM! 0 0 ­719.43 700 234 34 34 34 34 34 34 34 34 34 30 90 #NUM! 234 195 195 195 195 195 195 195 195 195 234 #NUM! 0 #NUM! 2355.66 0 1737.2 3640.3 #NUM! 5016.16 8514 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! ­30935.49 #NUM! 4680 567.8 601.8 865.64 1031.39 531.42 1031.39 736.1 1152.6 442 600 3870 #NUM! 3907.8 3451.5 4964.7 5915.33 3047.85 5915.33 4221.75 4221.75 4221.75 #NUM! #NUM! #NUM! 0 798.17 214.15 0 40.4 84.66 283.58 456.01 198 #NUM! #NUM! 586.26 #NUM! 269.55 #NUM! 0 0 ­719.43 700 234 34 34 34 34 34 34 34 34 34 30 90 #NUM! 234 195 195 195 195 195 195 195 195 195 234 #NUM! 0 #NUM! 2355.66 0 1737.2 3640.3 #NUM! 5016.16 8514 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! ­30935.49 #NUM! 4680 567.8 601.8 865.64 1031.39 531.42 1031.39 736.1 1152.6 442 600 3870 #NUM! 3907.8 3451.5 4964.7 5915.33 3047.85 5915.33 4221.75 4221.75 4221.75 #NUM! #NUM! #NUM! Max 0 798.17 214.15 0 40.4 84.66 283.58 456.01 198 #NUM! #NUM! 586.26 #NUM! 269.55 #NUM! 0 0 ­719.43 700 234 34 34 34 34 34 34 34 34 34 30 90 #NUM! 234 195 195 195 195 195 195 195 195 195 234 #NUM! 0 #NUM! 2355.66 0 1737.2 3640.3 #NUM! 5016.16 8514 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! ­30935.49 #NUM! 4680 567.8 601.8 865.64 1031.39 531.42 1031.39 736.1 1152.6 442 600 3870 #NUM! 3907.8 3451.5 4964.7 5915.33 3047.85 5915.33 4221.75 4221.75 4221.75 #NUM! #NUM! #NUM! 0 798.17 214.15 0 40.4 84.66 283.58 456.01 198 #NUM! #NUM! 586.26 #NUM! 269.55 #NUM! 0 0 ­719.43 700 234 34 34 34 34 34 34 34 34 34 30 90 #NUM! 234 0 0 0 0 0 0 0 0 0 0 #NUM! 0 #NUM! 2355.66 0 1737.2 3640.3 #NUM! 5016.16 8514 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! ­30935.49 #NUM! 4680 567.8 601.8 865.64 1031.39 531.42 1031.39 736.1 1152.6 442 600 3870 #NUM! 3907.8 0 0 0 0 0 0 0 0 0 0 #NUM! 0 798.17 214.15 0 40.4 84.66 283.58 456.01 198 #NUM! #NUM! 586.26 #NUM! 269.55 #NUM! 0 0 ­719.43 700 234 34 34 34 34 34 34 34 34 34 30 90 #NUM! 0 0 0 0 0 0 0 0 0 0 0 #NUM! Add Crew Add Passenger Min #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! Land 2600 2000 1716 1.4 518.69 2116.2 0 0 0 36152 82346 32.2 389.99 470.674 50.98 511.57 1967.51 0 1108.6 0.49 0.25 277.15 9.38 11.45 #NUM! #NUM! 0.67 #NUM! #NUM! 126314070.8 #NUM! #DIV/0! 3916080.0 11076347.0 17513242.4 Wf/W0 0.35 Runway 1 x y Runway 2 x y #NUM! 0 1 100 0 1 3600 2000 #NUM! 0.76 2 0 ­5000 2 3700 ­3000 #NUM! 2.76 3 ­300 0 3 4000 2000 #NUM! 32.76 4 ­180 3000 4 3880 5000 #NUM! 3442.56 1 100 0 1 3600 2000 #NUM! 3462.56 #NUM! 3463.51 Drag Coeff. form factor Fuselage Wing Nacelles 1.17 #NUM! 1.16 wetted area interference factor 922.6 #NUM! 0 1 1 1 ft/s Wind Factor 50 Cl CdTO CdC CdL 22290718.4 0.00206025 #NUM! #DIV/0! 0.00350592 0.00295512 0.00275020 0.00265018 #NUM! #NUM! 0.00000000 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! 31000 29000 27000 25000 23000 21000 19000 17000 15000 20 22 24 26 28 30 32 34 36 38 40 Crew Off Moment From Zero #NUM! Point #NUM! 0 Weight #NUM! #NUM! 0 Add FuelMoment From Zero #NUM! Point #NUM! 0 Weight #NUM! #NUM! 0 Add Crew Moment From Zero #NUM! Point #NUM! 0 Weight #NUM! #NUM! 0 Add Passenger Moment From Zero #NUM! Point #NUM! 0 0 #NUM! 2355.66 0 1737.2 3640.3 #NUM! 5016.16 8514 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! ­30935.49 #NUM! 4680 567.8 601.8 865.64 1031.39 531.42 1031.39 736.1 1152.6 442 600 3870 #NUM! 3907.8 0 0 0 0 0 0 0 0 0 0 #NUM! 0 798.17 214.15 0 40.4 84.66 283.58 456.01 198 #NUM! #NUM! 586.26 #NUM! 269.55 #NUM! 0 0 ­719.43 700 234 34 34 34 34 34 34 34 34 34 30 90 #NUM! 0 0 0 0 0 0 0 0 0 0 0 #NUM! 0 #NUM! 2355.66 0 1737.2 3640.3 #NUM! 5016.16 8514 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! ­30935.49 #NUM! 4680 567.8 601.8 865.64 1031.39 531.42 1031.39 736.1 1152.6 442 600 3870 #NUM! 3907.8 0 0 0 0 0 0 0 0 0 0 #NUM! 0 798.17 214.15 0 40.4 84.66 283.58 456.01 198 #NUM! #NUM! 586.26 #NUM! 269.55 #NUM! 0 0 ­719.43 700 234 34 34 34 34 34 34 34 34 34 30 90 #NUM! 234 0 0 0 0 0 0 0 0 0 0 #NUM! 0 #NUM! 2355.66 0 1737.2 3640.3 #NUM! 5016.16 8514 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! ­30935.49 #NUM! 4680 567.8 601.8 865.64 1031.39 531.42 1031.39 736.1 1152.6 442 600 3870 #NUM! 3907.8 0 0 0 0 0 0 0 0 0 0 #NUM! 0 798.17 214.15 0 40.4 84.66 283.58 456.01 198 #NUM! #NUM! 586.26 #NUM! 269.55 #NUM! 0 0 ­719.43 700 234 34 34 34 34 34 34 34 34 34 30 90 #NUM! 234 195 195 195 195 195 195 195 195 195 234 #NUM! 0 #NUM! 2355.66 0 1737.2 3640.3 #NUM! 5016.16 8514 #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! #NUM! ­30935.49 #NUM! 4680 567.8 601.8 865.64 1031.39 531.42 1031.39 736.1 1152.6 442 600 3870 #NUM! 3907.8 3451.5 4964.7 5915.33 3047.85 5915.33 4221.75 4221.75 4221.75 #NUM! #NUM! #NUM! #NUM! 3479.51 #NUM! 3679.51 #NUM! 3699.51 #NUM! 3700 ...
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