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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(ah93w300-il) AH 93-W-300 | Althaus AH 93-W-300 airfoil for use on wind turbines (W) Max thickness 30% at 27.9% chord Max camber 1.6% at 72.1% 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 |
(n63412-il) NACA 63-412 AIRFOIL | NACA 63(1)-412 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah93w300-il,ah81k144-il,n63412-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah93w300-il | 50,000 | 9 | 4.2 at α=-2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w300-il | 50,000 | 5 | 5.4 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w300-il | 100,000 | 9 | 17.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w300-il | 100,000 | 5 | 27.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w300-il | 200,000 | 9 | 42.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w300-il | 200,000 | 5 | 41 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w300-il | 500,000 | 9 | 61.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w300-il | 500,000 | 5 | 58.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w300-il | 1,000,000 | 9 | 80.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w300-il | 1,000,000 | 5 | 74.8 at α=6° | 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 | |
| n63412-il | 50,000 | 9 | 36.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63412-il | 50,000 | 5 | 36 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63412-il | 100,000 | 9 | 56.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63412-il | 100,000 | 5 | 54.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63412-il | 200,000 | 9 | 77.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63412-il | 200,000 | 5 | 70.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63412-il | 500,000 | 9 | 99.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63412-il | 500,000 | 5 | 88.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63412-il | 1,000,000 | 9 | 115.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63412-il | 1,000,000 | 5 | 98.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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