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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(joukowsk-il) 12% JOUKOWSKI AIRFOIL | 12% Joukowski airfoil Max thickness 11.8% at 25% chord Max camber 0% at 9.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (joukowsk-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| joukowsk-il | 50,000 | 9 | 22.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk-il | 50,000 | 5 | 26.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk-il | 100,000 | 9 | 34.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk-il | 100,000 | 5 | 37.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk-il | 200,000 | 9 | 47.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk-il | 200,000 | 5 | 48.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk-il | 500,000 | 9 | 65.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk-il | 500,000 | 5 | 65.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk-il | 1,000,000 | 9 | 80.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk-il | 1,000,000 | 5 | 79.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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