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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(e1210-il) EPPLER 1210 AIRFOIL | Eppler E1210 general aviation airfoil Max thickness 15.9% at 21.1% chord Max camber 5.2% at 33.3% chord | Remove Airfoil details Airfoil plotter |
(kenmar-il) KENNEDY AND MARSDEN AIRFOIL | University of Alberta/Kennedy and Marsden high lift airfoil Max thickness 27.9% at 31% chord Max camber 7.7% at 36.9% chord | Remove Airfoil details Airfoil plotter |
(k1-il) NYU/GRUMMAN K-1 AIRFOIL | NYU/Grumman K-1 transonic airfoil (GAC .75-.63-11.6) Max thickness 11.6% at 33% chord Max camber 1.9% at 75% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e1210-il,kenmar-il,k1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1210-il | 50,000 | 9 | 8.9 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 50,000 | 5 | 25.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 100,000 | 9 | 35.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 100,000 | 5 | 45.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 200,000 | 9 | 60.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 200,000 | 5 | 65.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 500,000 | 9 | 92.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 500,000 | 5 | 93.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 1,000,000 | 9 | 119.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 1,000,000 | 5 | 117.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 50,000 | 9 | 3 at α=16° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 50,000 | 5 | 3.5 at α=15° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 100,000 | 9 | 3 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 100,000 | 5 | 4.7 at α=-8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 200,000 | 9 | 5.1 at α=-7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 200,000 | 5 | 17.1 at α=-0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 500,000 | 9 | 28.3 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 500,000 | 5 | 59 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 1,000,000 | 9 | 70.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 1,000,000 | 5 | 97.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k1-il | 50,000 | 9 | 30.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k1-il | 50,000 | 5 | 29.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k1-il | 100,000 | 9 | 39.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k1-il | 100,000 | 5 | 38.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k1-il | 200,000 | 9 | 53.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k1-il | 200,000 | 5 | 49.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k1-il | 500,000 | 9 | 73.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k1-il | 500,000 | 5 | 63.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k1-il | 1,000,000 | 9 | 80.7 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k1-il | 1,000,000 | 5 | 76.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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