Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(e396-il) EPPLER 396 AIRFOIL | Eppler E396 human powered aircraft airfoil Max thickness 13.1% at 29.5% chord Max camber 5.4% at 52.1% chord | Remove Airfoil details Airfoil plotter |
(e329-il) EPPLER 329 AIRFOIL | Eppler E329 flying wing airfoil Max thickness 13.5% at 30.6% chord Max camber 3.5% at 25.7% chord | Remove Airfoil details Airfoil plotter |
(c5a-il) LOCKHEED C-5A BL0 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 13.1% at 40% chord Max camber 0.7% at 85% chord | Remove Airfoil details Airfoil plotter |
(c141f-il) LOCKHEED C-141 BL958.89 AIRFOIL | Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10% at 40.2% chord Max camber 2.3% at 45.1% chord | Remove Airfoil details Airfoil plotter |
(e682-il) EPPLER 682 AIRFOIL | Eppler E682 sailplane airfoil Max thickness 15.3% at 40.4% chord Max camber 2.9% at 40.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e396-il,e329-il,c5a-il,c141f-il,e682-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e396-il | 50,000 | 9 | 25.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 50,000 | 5 | 22.7 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e396-il | 100,000 | 9 | 54.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 100,000 | 5 | 57.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e396-il | 200,000 | 9 | 89.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 200,000 | 5 | 90.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e396-il | 500,000 | 9 | 135.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 500,000 | 5 | 128.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e396-il | 1,000,000 | 9 | 169.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 1,000,000 | 5 | 148 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e329-il | 50,000 | 9 | 17.3 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e329-il | 50,000 | 5 | 27.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e329-il | 100,000 | 9 | 37 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e329-il | 100,000 | 5 | 47.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e329-il | 200,000 | 9 | 63.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e329-il | 200,000 | 5 | 66.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e329-il | 500,000 | 9 | 94.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e329-il | 500,000 | 5 | 91.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e329-il | 1,000,000 | 9 | 116.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e329-il | 1,000,000 | 5 | 110.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 50,000 | 9 | 27.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 50,000 | 5 | 27.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 100,000 | 9 | 41.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 100,000 | 5 | 32.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 200,000 | 9 | 44.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 200,000 | 5 | 40.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 500,000 | 9 | 56.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 500,000 | 5 | 55.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 1,000,000 | 9 | 68.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 1,000,000 | 5 | 72.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 50,000 | 9 | 34.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 50,000 | 5 | 32.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 100,000 | 9 | 50.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 100,000 | 5 | 46.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 200,000 | 9 | 69.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 200,000 | 5 | 59.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 500,000 | 9 | 89 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 500,000 | 5 | 70 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 1,000,000 | 9 | 89.7 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 1,000,000 | 5 | 86.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e682-il | 50,000 | 9 | 25.1 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 50,000 | 5 | 21.5 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e682-il | 100,000 | 9 | 43.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 100,000 | 5 | 37.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e682-il | 200,000 | 9 | 75.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 200,000 | 5 | 58.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e682-il | 500,000 | 9 | 91.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 500,000 | 5 | 87.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e682-il | 1,000,000 | 9 | 115.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 1,000,000 | 5 | 105.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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