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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(ames02-il) NASA/AMES A-02 AIRFOIL | NASA/AMES/Hicks A-02 transonic rotorcraft airfoil Max thickness 7.7% at 30% chord Max camber 0.5% at 12.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ames02-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ames02-il | 50,000 | 9 | 24.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 50,000 | 5 | 22.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames02-il | 100,000 | 9 | 31.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 100,000 | 5 | 31.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames02-il | 200,000 | 9 | 37.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 200,000 | 5 | 41.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames02-il | 500,000 | 9 | 54.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 500,000 | 5 | 58.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames02-il | 1,000,000 | 9 | 69.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 1,000,000 | 5 | 72.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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