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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(usa45m-il) USA 45 M AIRFOIL | USA-45M airfoil Max thickness 11.6% at 30% chord Max camber 3.3% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa45m-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa45m-il | 50,000 | 9 | 20.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa45m-il | 50,000 | 5 | 29.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa45m-il | 100,000 | 9 | 45.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa45m-il | 100,000 | 5 | 48 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa45m-il | 200,000 | 9 | 65.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa45m-il | 200,000 | 5 | 66.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa45m-il | 500,000 | 9 | 93.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa45m-il | 500,000 | 5 | 90.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa45m-il | 1,000,000 | 9 | 115.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa45m-il | 1,000,000 | 5 | 108.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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