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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(joukowsk0021-jf) Joukovsky f=0% t=21% | Joukowski 21% symmetrical airfoil Max thickness 21% at 26.6% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (joukowsk0021-jf)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| joukowsk0021-jf | 50,000 | 9 | 2.5 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0021-jf | 50,000 | 5 | 17.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0021-jf | 100,000 | 9 | 29.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0021-jf | 100,000 | 5 | 32.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0021-jf | 200,000 | 9 | 46.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0021-jf | 200,000 | 5 | 45.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0021-jf | 500,000 | 9 | 66.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0021-jf | 500,000 | 5 | 64.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0021-jf | 1,000,000 | 9 | 84.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0021-jf | 1,000,000 | 5 | 78.9 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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