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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(goe244-il) GOE 244 (MVA PR.4) AIRFOIL | Gottingen 244 (MVA PR.4) airfoil Max thickness 17.7% at 19.6% chord Max camber 10% at 49.6% 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 |
(s802-nr) NREL's S802 Airfoil | NREL HAWT airfoil S802 tip Not recommended Max thickness 11.5% at 37.9% chord Max camber 3.8% at 47.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe244-il,goe239-il,s802-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe244-il | 50,000 | 9 | 7.9 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe244-il | 50,000 | 5 | 25 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe244-il | 100,000 | 9 | 50.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe244-il | 100,000 | 5 | 47.8 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe244-il | 200,000 | 9 | 73.3 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe244-il | 200,000 | 5 | 64.3 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe244-il | 500,000 | 9 | 92.3 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe244-il | 500,000 | 5 | 79.5 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe244-il | 1,000,000 | 9 | 105.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe244-il | 1,000,000 | 5 | 98.8 at α=2.5° | 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 | |
| s802-nr | 50,000 | 9 | 36.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 50,000 | 5 | 33.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 100,000 | 9 | 61 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 100,000 | 5 | 60.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 200,000 | 9 | 91.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 200,000 | 5 | 85.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 500,000 | 9 | 124.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 500,000 | 5 | 113.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 1,000,000 | 9 | 149.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 1,000,000 | 5 | 132.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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