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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(usa25-il) USA 25 AIRFOIL | USA-25 airfoil Max thickness 8.3% at 19.9% chord Max camber 5.2% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(usa98-il) USA 98 AIRFOIL | USA-98 airfoil Max thickness 14.3% at 30% chord Max camber 6.4% at 50% chord | Remove Airfoil details Airfoil plotter |
(usa34-il) USA 34 AIRFOIL | USA-34 airfoil Max thickness 18% at 29.5% chord Max camber 7.7% at 39.5% chord | Remove Airfoil details Airfoil plotter |
(naca4412-il) NACA 4412 | NACA 4412 airfoil Max thickness 12% at 30% chord Max camber 4% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa25-il,usa98-il,usa34-il,naca4412-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa25-il | 50,000 | 9 | 25.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 50,000 | 5 | 35.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa25-il | 100,000 | 9 | 52.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 100,000 | 5 | 54.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa25-il | 200,000 | 9 | 74.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 200,000 | 5 | 73 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa25-il | 500,000 | 9 | 102 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 500,000 | 5 | 97.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa25-il | 1,000,000 | 9 | 124.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 1,000,000 | 5 | 106.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 50,000 | 9 | 8.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 50,000 | 5 | 26.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 100,000 | 9 | 54.2 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 100,000 | 5 | 59.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 200,000 | 9 | 84.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 200,000 | 5 | 84.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 500,000 | 9 | 120.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 500,000 | 5 | 112.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 1,000,000 | 9 | 147.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 1,000,000 | 5 | 124.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 50,000 | 9 | 4 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 50,000 | 5 | 9.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 100,000 | 9 | 9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 100,000 | 5 | 40.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 200,000 | 9 | 66.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 200,000 | 5 | 60.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 500,000 | 9 | 86.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 500,000 | 5 | 75 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 1,000,000 | 9 | 104.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 1,000,000 | 5 | 87.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 50,000 | 9 | 33.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 50,000 | 5 | 36.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 100,000 | 9 | 56.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 100,000 | 5 | 57.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 200,000 | 9 | 78.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 200,000 | 5 | 76.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 500,000 | 9 | 107.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 500,000 | 5 | 101.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 1,000,000 | 9 | 129.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 1,000,000 | 5 | 119.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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