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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(naca0024-il) NACA 0024 | NACA 0024 airfoil Max thickness 24% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(eiffel10-il) Eiffel 10 (Wright) - 1903 Wright Flyer airfoil | Eiffel 10 (Wright) - 1903 Wright Flyer airfoil Max thickness 2.7% at 0% chord Max camber 6.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(ah81k144-il) AH 81-K-144/17 | Althaus AH 81-K-144/17 airfoil for use with flaps (K) Max thickness 14.5% at 40.2% chord Max camber 4.2% at 46.7% 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 (naca0024-il,eiffel10-il,ah81k144-il,ah93w257-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca0024-il | 50,000 | 9 | 15.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 50,000 | 5 | 21.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 100,000 | 9 | 34.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 100,000 | 5 | 30.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 200,000 | 9 | 43 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 200,000 | 5 | 37 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 500,000 | 9 | 52.1 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 500,000 | 5 | 50.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 1,000,000 | 9 | 68.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 1,000,000 | 5 | 64.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel10-il | 50,000 | 9 | 25.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel10-il | 50,000 | 5 | 27 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel10-il | 100,000 | 9 | 27.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel10-il | 100,000 | 5 | 29.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel10-il | 200,000 | 9 | 28.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel10-il | 200,000 | 5 | 34.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel10-il | 500,000 | 9 | 32.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel10-il | 500,000 | 5 | 38.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel10-il | 1,000,000 | 9 | 36.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel10-il | 1,000,000 | 5 | 45.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81k144-il | 50,000 | 9 | 17.8 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81k144-il | 50,000 | 5 | 16.6 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81k144-il | 100,000 | 9 | 29.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81k144-il | 100,000 | 5 | 30.5 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81k144-il | 200,000 | 9 | 62.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81k144-il | 200,000 | 5 | 67.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81k144-il | 500,000 | 9 | 129.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81k144-il | 500,000 | 5 | 117.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81k144-il | 1,000,000 | 9 | 156.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81k144-il | 1,000,000 | 5 | 145.3 at α=5.25° | 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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