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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(usa32-il) USA 32 AIRFOIL | USA-32 airfoil Max thickness 14.7% at 19.8% chord Max camber 9.3% at 39.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa32-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa32-il | 50,000 | 9 | 4.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa32-il | 50,000 | 5 | 13.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa32-il | 100,000 | 9 | 39.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa32-il | 100,000 | 5 | 41 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa32-il | 200,000 | 9 | 64.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa32-il | 200,000 | 5 | 50.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa32-il | 500,000 | 9 | 68.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa32-il | 500,000 | 5 | 59.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa32-il | 1,000,000 | 9 | 76.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa32-il | 1,000,000 | 5 | 67.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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