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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(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 |
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Polars for (ah81k144-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
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