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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(ah79k143-il) AH 79-K-143/18 | Althaus AH 79-K-143/18 airfoil for use with flaps (K) Max thickness 14.3% at 40.2% chord Max camber 2.9% at 40.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah79k143-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah79k143-il | 50,000 | 9 | 20.5 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79k143-il | 50,000 | 5 | 19.8 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79k143-il | 100,000 | 9 | 39 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79k143-il | 100,000 | 5 | 37.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79k143-il | 200,000 | 9 | 76.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79k143-il | 200,000 | 5 | 62.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79k143-il | 500,000 | 9 | 90.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79k143-il | 500,000 | 5 | 86.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79k143-il | 1,000,000 | 9 | 110.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79k143-il | 1,000,000 | 5 | 107.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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