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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(usa35a-il) USA 35 A AIRFOIL | USA-35A airfoil Max thickness 18.2% at 29.4% chord Max camber 6.4% at 39.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa35a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa35a-il | 50,000 | 9 | 4.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35a-il | 50,000 | 5 | 20.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35a-il | 100,000 | 9 | 35.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35a-il | 100,000 | 5 | 46.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35a-il | 200,000 | 9 | 66.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35a-il | 200,000 | 5 | 67.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35a-il | 500,000 | 9 | 97.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35a-il | 500,000 | 5 | 92.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35a-il | 1,000,000 | 9 | 122.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35a-il | 1,000,000 | 5 | 109.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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