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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(usa26-il) USA 26 AIRFOIL | USA-26 airfoil Max thickness 9.8% at 19.9% chord Max camber 4.3% at 39.9% 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 |
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Polars for (usa26-il,usa34-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa26-il | 50,000 | 9 | 27.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa26-il | 50,000 | 5 | 35.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa26-il | 100,000 | 9 | 49.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa26-il | 100,000 | 5 | 52.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa26-il | 200,000 | 9 | 69.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa26-il | 200,000 | 5 | 69.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa26-il | 500,000 | 9 | 95.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa26-il | 500,000 | 5 | 92.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa26-il | 1,000,000 | 9 | 117.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa26-il | 1,000,000 | 5 | 108.7 at α=5.5° | 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 | |
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