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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(ah95160-il) AH 95-160 | Althaus AH 95-160 airfoil Max thickness 16% at 38.9% chord Max camber 5.6% at 44.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah95160-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah95160-il | 50,000 | 9 | 5.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 50,000 | 5 | 12.8 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 100,000 | 9 | 23.9 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 100,000 | 5 | 24.8 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 200,000 | 9 | 65.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 200,000 | 5 | 73.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 500,000 | 9 | 130.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 500,000 | 5 | 128.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 1,000,000 | 9 | 173.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 1,000,000 | 5 | 163.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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