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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(usa48-il) USA 48 AIRFOIL | USA-48 airfoil Max thickness 14.9% at 30% chord Max camber 2.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa48-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa48-il | 50,000 | 9 | 24.1 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa48-il | 50,000 | 5 | 30.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa48-il | 100,000 | 9 | 49.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa48-il | 100,000 | 5 | 49.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa48-il | 200,000 | 9 | 69.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa48-il | 200,000 | 5 | 63.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa48-il | 500,000 | 9 | 85.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa48-il | 500,000 | 5 | 65.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa48-il | 1,000,000 | 9 | 81.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa48-il | 1,000,000 | 5 | 73.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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