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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(ah93k132-il) AH 93-K-132/15 | Althaus AH 93-K-132/15 airfoil for use with flaps (K) Max thickness 13.2% at 41.2% chord Max camber 3.5% at 41.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah93k132-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah93k132-il | 50,000 | 9 | 25.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k132-il | 50,000 | 5 | 22.8 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93k132-il | 100,000 | 9 | 42.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k132-il | 100,000 | 5 | 40 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93k132-il | 200,000 | 9 | 73.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k132-il | 200,000 | 5 | 71.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93k132-il | 500,000 | 9 | 114.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k132-il | 500,000 | 5 | 99.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93k132-il | 1,000,000 | 9 | 134.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k132-il | 1,000,000 | 5 | 103.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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