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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(clarkk-il) CLARK K AIRFOIL | CLARK K airfoil Max thickness 11.7% at 29.7% chord Max camber 3.3% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(e1211-il) EPPLER 1211 AIRFOIL | Eppler E1211 general aviation airfoil Max thickness 18% at 20.9% chord Max camber 4.4% at 37.7% chord | Remove Airfoil details Airfoil plotter |
(coanda1-il) Coanda 1 | Coanda 1 airfoil Max thickness 5.7% at 30% chord Max camber 2.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(clarkv-il) CLARK V AIRFOIL | CLARK V airfoil Max thickness 11.6% at 30% chord Max camber 3.4% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (clarkk-il,e1211-il,coanda1-il,clarkv-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| clarkk-il | 50,000 | 9 | 32.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 50,000 | 5 | 36.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 100,000 | 9 | 54.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 100,000 | 5 | 54.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 200,000 | 9 | 75.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 200,000 | 5 | 71.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 500,000 | 9 | 102.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 500,000 | 5 | 91.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 1,000,000 | 9 | 121.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 1,000,000 | 5 | 104.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1211-il | 50,000 | 9 | 6 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 50,000 | 5 | 24.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1211-il | 100,000 | 9 | 33.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 100,000 | 5 | 44 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1211-il | 200,000 | 9 | 58.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 200,000 | 5 | 62.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1211-il | 500,000 | 9 | 89 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 500,000 | 5 | 89.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1211-il | 1,000,000 | 9 | 115.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 1,000,000 | 5 | 113.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda1-il | 50,000 | 9 | 38 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 50,000 | 5 | 37.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda1-il | 100,000 | 9 | 54.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 100,000 | 5 | 47.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda1-il | 200,000 | 9 | 60.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 200,000 | 5 | 45.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda1-il | 500,000 | 9 | 63.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 500,000 | 5 | 51.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda1-il | 1,000,000 | 9 | 60.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 1,000,000 | 5 | 57.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkv-il | 50,000 | 9 | 35.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 50,000 | 5 | 36.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkv-il | 100,000 | 9 | 57.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 100,000 | 5 | 56.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkv-il | 200,000 | 9 | 80.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 200,000 | 5 | 75.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkv-il | 500,000 | 9 | 110.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 500,000 | 5 | 95.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkv-il | 1,000,000 | 9 | 129.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 1,000,000 | 5 | 105.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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