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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(ah6407-il) AH-6-40-7 AIRFOIL | Althaus AH 6-407 airfoil Max thickness 6.9% at 20% chord Max camber 5.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah6407-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah6407-il | 50,000 | 9 | 41.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 50,000 | 5 | 46.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 100,000 | 9 | 67.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 100,000 | 5 | 67.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 200,000 | 9 | 91.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 200,000 | 5 | 85.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 500,000 | 9 | 119.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 500,000 | 5 | 104 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 1,000,000 | 9 | 131.3 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 1,000,000 | 5 | 121.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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