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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(goe269-il) GOE 269 AIRFOIL | Gottingen 269 airfoil Max thickness 6.6% at 29.9% chord Max camber 5% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(s812-nr) NREL's S812 Airfoil | NREL HAWT airfoil S812 primary Max thickness 21% at 39.6% chord Max camber 1.6% at 77% chord | Remove Airfoil details Airfoil plotter |
(goe239-il) GOE 239 (MVA H.31) AIRFOIL | Gottingen 239 (MVA H.31) airfoil Max thickness 11.2% at 19.8% chord Max camber 6% at 39.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe269-il,s812-nr,goe239-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe269-il | 50,000 | 9 | 36.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe269-il | 50,000 | 5 | 43.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe269-il | 100,000 | 9 | 59.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe269-il | 100,000 | 5 | 61.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe269-il | 200,000 | 9 | 80.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe269-il | 200,000 | 5 | 79.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe269-il | 500,000 | 9 | 107.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe269-il | 500,000 | 5 | 102.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe269-il | 1,000,000 | 9 | 127.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe269-il | 1,000,000 | 5 | 115.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s812-nr | 50,000 | 9 | 17.4 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 50,000 | 5 | 14.2 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s812-nr | 100,000 | 9 | 23.9 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 100,000 | 5 | 25.8 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s812-nr | 200,000 | 9 | 56.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 200,000 | 5 | 59.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s812-nr | 500,000 | 9 | 92.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 500,000 | 5 | 87.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s812-nr | 1,000,000 | 9 | 116.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 1,000,000 | 5 | 105.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe239-il | 50,000 | 9 | 17.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe239-il | 50,000 | 5 | 38.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe239-il | 100,000 | 9 | 54.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe239-il | 100,000 | 5 | 60.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe239-il | 200,000 | 9 | 81.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe239-il | 200,000 | 5 | 83.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe239-il | 500,000 | 9 | 118.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe239-il | 500,000 | 5 | 113 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe239-il | 1,000,000 | 9 | 144.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe239-il | 1,000,000 | 5 | 125.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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