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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(ah80136-il) AH 80-136 | Althaus AH 80-136 airfoil Max thickness 13.5% at 33.9% chord Max camber 3.4% at 33.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah80136-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah80136-il | 50,000 | 9 | 14.9 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80136-il | 50,000 | 5 | 13.8 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80136-il | 100,000 | 9 | 32.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80136-il | 100,000 | 5 | 33.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80136-il | 200,000 | 9 | 71 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80136-il | 200,000 | 5 | 71.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80136-il | 500,000 | 9 | 110.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80136-il | 500,000 | 5 | 105.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80136-il | 1,000,000 | 9 | 138.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80136-il | 1,000,000 | 5 | 127.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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