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choisizingconcept_carpet_plot(1)

choisizingconcept_carpet_plot(1) - Fuselage Nose Length...

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Main  Fuselage Wing Nose Fuselage Empannag End Wing Canard Yehudi Tail Vertical Length 11 27 13 0 Wing Area #NUM! 0 30 100 100 y-location -2 0 0 2 Leading Edge Angle 30 25 #NUM! 25 30 diameter 0 7 7 0 Sweep Angle #NUM! #DIV/0! #NUM! 21.78 22.33 Number of Passengers 9 Taper Ratio 0.5 0.6 0 0.5 0.5 Number of Flight Crew 2 Aspect Ratio 7.8 3 12 5 2 Mcruise  0.800 x-Location 22 3 #NUM! 37 36 Center of Gravity x-location #NUM! ft y-Location -3 -2 -3 3.5 Neutral Point x-location #NUM! ft NACA 2414 Static Margin #NUM! Chord  #NUM! #NUM! Empty Weight  #NUM! lb Total Weight #NUM! lb Thrust To Weight Ratio 0.3 Wing Loading 70 0 5 10 15 20 25 30 35 40 45 50 -7 3 13 -30 -20 -10 0 10 20 30 -5 5 15 0 5 10 15 20 25 30 35 40 45 50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 80 90 100110120130 0 0.1 0.2 0.3 0.4 0.5 0.6 Top of climb (1g steady, level flight, M = 0.80 @ h=45K, ser- vice 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 seg- ment climb gradient above h = 5K, +15° hot day W0/S & TSL/ W0 Value 0 2 4 6 8 10 12 -2 0 2 4
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Engine Misson Sketch Unducted Fan Number of Engine 2 Location Length 2 3 4 0 0.5 x-location 38 40 43 47 47.5 y-location 3.5 0 0 0 0 z-location 7.5 7.5 7.5 7.5 7.5 diameter 2.09 4 4.5 2.09 4 Performance Thrust 2000 lbf Weight 237 lbs Area 2.662 ft^2 Diameter 2.089 ft Wind 50 ft/s Length 4.26 ft Flight Time 7.71 hrs Volume 5.89 ft^3 Unducted Fan Number of Engine 1 Location Length 2 3 4 0 0.5 x-location 40 42 45 49 49.5 y-location 0 0 0 0 0 z-location 6.5 6.5 6.5 6.5 6.5 diameter ### 5 5 ### 4 Performance Thrust #NUM! lbf Weight #NUM! lbs Area #NUM! ft^2 Diameter #NUM! ft Length #NUM! ft Volume #NUM! ft^3 Fuel Consum Fuel Density 6.8 lb/Gal Fuel Price 4.42 $/Gallon Mission Fuel Price #NUM! $ -500 0 500 1000 1500 -5000 5000 15000 25000 35000 45000
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2000 2500 3000 3500 4000 4500
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Fuselage Nose FuselageEmpann End Length 11 27 13 0 total length 51 Wing Area CenterLine x 0 11 38 51 diameter 7 Sweep Angle Start y -2 0 0 2 Fineness ratio 7.29 Taper Ratio diameter d 0 7 7 0 wetted area 922.6 Aspect Ratio Volume 141.11 ### 166.77 form factor 1.17 x-Location Wetted Area 126.93 593.76 148.03 interference facto 1 y-Location 0 b/2 C1+C2 d C1 C2 C1quarter C2quarter C1qLocation C2qLoaction Sweep angle angle Wetted Area sweep correction Form Factor interference facto Mean Chord Leng Center of Pressur Partial Lift Moment CenterLine Total Lif x y radius y-top y-bottomz-top z-bottom #NUM! Nose 0 0 -2 0 -2 -2 0 0 1 2.2 -1.6 0.7 -0.9 -2.3 0.7 -0.7 Wing 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 Fuselage 6 11 0 3.5 3.5 -3.5 3.5 -3.5 Canard 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 ehudi 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 0 5 10 15 20 25 30 35 40 45 50 -15 -10 -5 0 5 10 15 0 5 10 15 20 25 30 35 40 45 50 -10 -5 0 5 10 -30 -20 -10 0 10 20 30 -5 0 5 10
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Tail 14 43.2 0.8 2.1 2.9 -1.3 2.1 -2.1 Ye 15 45.8 1.2 1.4 2.6 -0.2 1.4 -1.4 16 48.4 1.6 0.7 2.3 0.9 0.7 -0.7 Tail 17 51 2 0 2 2 0 0 Section 0 radius 0 y -2 Point # Angle y-positio z-position 0 0 0 -2 Vertical 1 0.39 0 -2 2 0.79 0 -2 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 1 radius 0.7 y -1.6 Point # Angle y-positio z-position 0 0 0 -0.9 1 0.39 0.27 -0.95 2 0.79 0.49 -1.11 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 0 0.5 1 -3 -2 -1 0 Colum n E -1 0 1 -3 -2 -1 0 Colu mn E 2
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Section 2 Point # Angle y-positio z-position 0 0 0 0.2 1 0.39 0.54 0.09 2 0.79 0.99 -0.21 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
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