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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(ah79100c-il) AH 79-100 C AIRFOIL | Althaus AH 79-100C airfoil Max thickness 9.9% at 30.9% chord Max camber 6.7% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah79100c-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah79100c-il | 50,000 | 9 | 32.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 50,000 | 5 | 31.5 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100c-il | 100,000 | 9 | 61.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 100,000 | 5 | 61.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100c-il | 200,000 | 9 | 97.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 200,000 | 5 | 97 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100c-il | 500,000 | 9 | 147.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 500,000 | 5 | 137.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100c-il | 1,000,000 | 9 | 183 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 1,000,000 | 5 | 161.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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