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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(usa22-il) USA 22 AIRFOIL | USA-22 airfoil Max thickness 9.1% at 19.9% chord Max camber 4.4% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(sp4621hp-po) SP4621HP | Saab-Pimenta High Performance low TE noise 100 m Diameter Wind Turbine Main Airfoil Max thickness 21.1% at 36.5% chord Max camber 3.9% at 64.1% chord | Remove Airfoil details Airfoil plotter |
(usa31-il) USA 31 AIRFOIL | USA-31 airfoil Max thickness 14.8% at 19.7% chord Max camber 9.3% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(ah93w257-il) AH 93-W-257 | Althaus AH 93-W-257 airfoil for use on wind turbines (W) Max thickness 25.7% at 30.9% chord Max camber 2.1% at 77.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa22-il,sp4621hp-po,usa31-il,ah93w257-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa22-il | 50,000 | 9 | 32.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 50,000 | 5 | 37.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa22-il | 100,000 | 9 | 53.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 100,000 | 5 | 55.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa22-il | 200,000 | 9 | 73 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 200,000 | 5 | 73.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa22-il | 500,000 | 9 | 99.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 500,000 | 5 | 96.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa22-il | 1,000,000 | 9 | 119.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 1,000,000 | 5 | 112.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sp4621hp-po | 200,000 | 9 | 68.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sp4621hp-po | 500,000 | 9 | 105 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sp4621hp-po | 1,000,000 | 9 | 131.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sp4621hp-po | 2,000,000 | 9 | 155.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sp4621hp-po | 5,000,000 | 9 | 178.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 50,000 | 9 | 4.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 50,000 | 5 | 14.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 100,000 | 9 | 34.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 100,000 | 5 | 40.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 200,000 | 9 | 62.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 200,000 | 5 | 54.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 500,000 | 9 | 76.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 500,000 | 5 | 69.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 1,000,000 | 9 | 88.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 1,000,000 | 5 | 79.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w257-il | 50,000 | 9 | 2.9 at α=14.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w257-il | 50,000 | 5 | 6.5 at α=17.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w257-il | 100,000 | 9 | 13.6 at α=16.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w257-il | 100,000 | 5 | 23.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w257-il | 200,000 | 9 | 49.6 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w257-il | 200,000 | 5 | 58.3 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w257-il | 500,000 | 9 | 92.5 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w257-il | 500,000 | 5 | 92.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w257-il | 1,000,000 | 9 | 120.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w257-il | 1,000,000 | 5 | 114.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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