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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(e852-il) EPPLER E852 AIRFOIL | Eppler E852 propeller airfoil Max thickness 10.1% at 37.2% chord Max camber 2.8% at 61.2% chord | Remove Airfoil details Airfoil plotter |
(e222-il) E222 (10.17%) | Eppler E222 low Reynolds number airfoil Max thickness 10.2% at 31.1% chord Max camber 2.1% at 55.3% chord | Remove Airfoil details Airfoil plotter |
(e212-il) E212 (10.55%) | Eppler E212 low Reynolds number airfoil Max thickness 10.6% at 27.5% chord Max camber 2.5% at 61.3% chord | Remove Airfoil details Airfoil plotter |
(goe264-il) GOE 264 AIRFOIL | Gottingen 264 airfoil Max thickness 6.4% at 20.2% chord Max camber 5.7% at 28.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e852-il,e222-il,e212-il,goe264-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e852-il | 50,000 | 9 | 36.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e852-il | 50,000 | 5 | 35.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e852-il | 100,000 | 9 | 58.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e852-il | 100,000 | 5 | 57.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e852-il | 200,000 | 9 | 84.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e852-il | 200,000 | 5 | 79.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e852-il | 500,000 | 9 | 119.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e852-il | 500,000 | 5 | 98.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e852-il | 1,000,000 | 9 | 132.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e852-il | 1,000,000 | 5 | 106.5 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 50,000 | 9 | 36.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 50,000 | 5 | 38.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 100,000 | 9 | 56.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 100,000 | 5 | 55.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 200,000 | 9 | 76.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 200,000 | 5 | 71.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 500,000 | 9 | 101.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 500,000 | 5 | 89.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 1,000,000 | 9 | 118.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 1,000,000 | 5 | 99.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e212-il | 50,000 | 9 | 38.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e212-il | 50,000 | 5 | 40.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e212-il | 100,000 | 9 | 59.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e212-il | 100,000 | 5 | 58.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e212-il | 200,000 | 9 | 81.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e212-il | 200,000 | 5 | 75.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e212-il | 500,000 | 9 | 108.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e212-il | 500,000 | 5 | 91.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e212-il | 1,000,000 | 9 | 119.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e212-il | 1,000,000 | 5 | 101 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe264-il | 50,000 | 9 | 32.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe264-il | 50,000 | 5 | 41.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe264-il | 100,000 | 9 | 59.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe264-il | 100,000 | 5 | 60.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe264-il | 200,000 | 9 | 79.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe264-il | 200,000 | 5 | 79.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe264-il | 500,000 | 9 | 106.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe264-il | 500,000 | 5 | 104.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe264-il | 1,000,000 | 9 | 126.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe264-il | 1,000,000 | 5 | 121.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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