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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(2032c-il) 20-32C AIRFOIL | Dillner 20-32-C low Reynolds number airfoil Max thickness 8% at 20% chord Max camber 6.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (2032c-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 2032c-il | 50,000 | 9 | 31.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| 2032c-il | 50,000 | 5 | 40.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 2032c-il | 100,000 | 9 | 54.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| 2032c-il | 100,000 | 5 | 58.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 2032c-il | 200,000 | 9 | 75.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| 2032c-il | 200,000 | 5 | 76.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 2032c-il | 500,000 | 9 | 103.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| 2032c-il | 500,000 | 5 | 103.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 2032c-il | 1,000,000 | 9 | 126.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| 2032c-il | 1,000,000 | 5 | 124.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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