Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(e210-il) E210 (13.64%) | Eppler E210 low Reynolds number airfoil Max thickness 13.6% at 32.1% chord Max camber 3.7% at 50.7% chord | Remove Airfoil details Airfoil plotter |
(curtisc72-il) Curtis C-72 | Curtis C-72 airfoil Max thickness 11.7% at 30% chord Max camber 3.8% at 50% chord | Remove Airfoil details Airfoil plotter |
(e838-il) EPPLER E838 HYDROFOIL AIRFOIL | Eppler E838 hydrofoil Max thickness 18.4% at 37.2% chord Max camber 0% at 46.5% chord | Remove Airfoil details Airfoil plotter |
(dae11-il) DAE-11 AIRFOIL | Drela DAE11 low Reynolds number airfoil Max thickness 12.8% at 32.8% chord Max camber 6.6% at 44.4% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e210-il,curtisc72-il,e838-il,dae11-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e210-il | 50,000 | 9 | 9.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 50,000 | 5 | 30.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 100,000 | 9 | 52.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 100,000 | 5 | 57.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 200,000 | 9 | 78.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 200,000 | 5 | 79.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 500,000 | 9 | 113 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 500,000 | 5 | 109 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 1,000,000 | 9 | 140.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 1,000,000 | 5 | 129.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| curtisc72-il | 50,000 | 9 | 29.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| curtisc72-il | 50,000 | 5 | 37.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| curtisc72-il | 100,000 | 9 | 54.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| curtisc72-il | 100,000 | 5 | 56.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| curtisc72-il | 200,000 | 9 | 76.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| curtisc72-il | 200,000 | 5 | 73.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| curtisc72-il | 500,000 | 9 | 103.4 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| curtisc72-il | 500,000 | 5 | 95.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| curtisc72-il | 1,000,000 | 9 | 121 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| curtisc72-il | 1,000,000 | 5 | 114.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 50,000 | 9 | 18.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 50,000 | 5 | 16.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 100,000 | 9 | 31.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 100,000 | 5 | 29.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 200,000 | 9 | 51.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 200,000 | 5 | 49.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 500,000 | 9 | 73.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 500,000 | 5 | 65 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 1,000,000 | 9 | 86.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 1,000,000 | 5 | 72.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 50,000 | 9 | 6.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 50,000 | 5 | 13.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 100,000 | 9 | 31.3 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 100,000 | 5 | 32.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 200,000 | 9 | 79 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 200,000 | 5 | 83.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 500,000 | 9 | 135.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 500,000 | 5 | 132.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 1,000,000 | 9 | 177.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 1,000,000 | 5 | 165 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||