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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(e1212-il) EPPLER E1212 AIRFOIL | Eppler E1212 general aviation airfoil Max thickness 17.7% at 23.4% chord Max camber 3.2% at 36.4% chord | Remove Airfoil details Airfoil plotter |
(e1214-il) EPPLER 1214 AIRFOIL | Eppler E1214 general aviation airfoil Max thickness 19.8% at 26.2% chord Max camber 2.1% at 30.4% chord | Remove Airfoil details Airfoil plotter |
(goe100-il) GOE 100 (SOPWITH) AIRFOIL | Gottingen 100 (Sopwith) airfoil Max thickness 6.6% at 20% chord Max camber 3.6% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(e1213-il) EPPLER 1213 AIRFOIL | Eppler E1213 general aviation airfoil Max thickness 17.4% at 22.1% chord Max camber 2.1% at 35.1% chord | Remove Airfoil details Airfoil plotter |
(m20-il) NACA M20 AIRFOIL | NACA/Munk M-20 airfoil Max thickness 8.2% at 30% chord Max camber 6.1% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e1212-il,e1214-il,goe100-il,e1213-il,m20-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1212-il | 50,000 | 9 | 7.1 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 50,000 | 5 | 23.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212-il | 100,000 | 9 | 32.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 100,000 | 5 | 41.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212-il | 200,000 | 9 | 55.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 200,000 | 5 | 59.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212-il | 500,000 | 9 | 84.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 500,000 | 5 | 85.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212-il | 1,000,000 | 9 | 109.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 1,000,000 | 5 | 107.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 50,000 | 9 | 3.1 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 50,000 | 5 | 18.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 100,000 | 9 | 25.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 100,000 | 5 | 36.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 200,000 | 9 | 48.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 200,000 | 5 | 54 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 500,000 | 9 | 78.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 500,000 | 5 | 80.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 1,000,000 | 9 | 105.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 1,000,000 | 5 | 103.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe100-il | 50,000 | 9 | 37.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 50,000 | 5 | 38 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe100-il | 100,000 | 9 | 54.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 100,000 | 5 | 50.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe100-il | 200,000 | 9 | 71.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 200,000 | 5 | 61.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe100-il | 500,000 | 9 | 88.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 500,000 | 5 | 73.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe100-il | 1,000,000 | 9 | 88.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 1,000,000 | 5 | 83.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 50,000 | 9 | 11.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 50,000 | 5 | 22.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 100,000 | 9 | 30.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 100,000 | 5 | 39.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 200,000 | 9 | 51.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 200,000 | 5 | 55.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 500,000 | 9 | 79.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 500,000 | 5 | 80.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 1,000,000 | 9 | 102.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 1,000,000 | 5 | 101.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 50,000 | 9 | 10.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 50,000 | 5 | 26.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 100,000 | 9 | 55.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 100,000 | 5 | 56.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 200,000 | 9 | 78.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 200,000 | 5 | 78 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 500,000 | 9 | 108.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 500,000 | 5 | 105.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 1,000,000 | 9 | 131.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 1,000,000 | 5 | 125.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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