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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(usa46-il) USA 46 AIRFOIL | USA-46 airfoil Max thickness 6.5% at 20% chord Max camber 2.2% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa46-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa46-il | 50,000 | 9 | 38.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa46-il | 50,000 | 5 | 38.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa46-il | 100,000 | 9 | 52.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa46-il | 100,000 | 5 | 51.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa46-il | 200,000 | 9 | 69 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa46-il | 200,000 | 5 | 63.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa46-il | 500,000 | 9 | 86.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa46-il | 500,000 | 5 | 75.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa46-il | 1,000,000 | 9 | 97.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa46-il | 1,000,000 | 5 | 80.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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