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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(ah79k132-il) AH 79-K-132/20 | Althaus AH 79-K-132/20 airfoil for use with flaps (K) Max thickness 13.2% at 40.2% chord Max camber 3.7% at 40.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah79k132-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah79k132-il | 50,000 | 9 | 21.8 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79k132-il | 50,000 | 5 | 22.4 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79k132-il | 100,000 | 9 | 47.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79k132-il | 100,000 | 5 | 45.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79k132-il | 200,000 | 9 | 79.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79k132-il | 200,000 | 5 | 78.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79k132-il | 500,000 | 9 | 115 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79k132-il | 500,000 | 5 | 100 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79k132-il | 1,000,000 | 9 | 130.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79k132-il | 1,000,000 | 5 | 116.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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