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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(ah7476-il) AH-7-47-6 AIRFOIL | Althaus AH 7-476 airfoil Max thickness 5.9% at 20% chord Max camber 6.2% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah7476-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah7476-il | 50,000 | 9 | 48.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah7476-il | 50,000 | 5 | 48.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah7476-il | 100,000 | 9 | 75.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah7476-il | 100,000 | 5 | 74.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah7476-il | 200,000 | 9 | 107.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah7476-il | 200,000 | 5 | 103.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah7476-il | 500,000 | 9 | 148.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah7476-il | 500,000 | 5 | 110.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah7476-il | 1,000,000 | 9 | 138.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah7476-il | 1,000,000 | 5 | 112.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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