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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(ah79100b-il) AH 79-100 B AIRFOIL | Althaus AH 79-100B airfoil Max thickness 10% at 30.9% chord Max camber 6.4% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah79100b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah79100b-il | 50,000 | 9 | 32.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 50,000 | 5 | 32.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 100,000 | 9 | 65.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 100,000 | 5 | 68.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 200,000 | 9 | 100 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 200,000 | 5 | 101 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 500,000 | 9 | 148.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 500,000 | 5 | 139.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 1,000,000 | 9 | 183.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 1,000,000 | 5 | 153.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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