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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(joukowsk0015-jf) Joukovsky f=0% t=15% | Joukowski 15% symmetrical airfoil Max thickness 15% at 24.6% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (joukowsk0015-jf)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| joukowsk0015-jf | 50,000 | 9 | 17.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0015-jf | 50,000 | 5 | 25.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0015-jf | 100,000 | 9 | 35 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0015-jf | 100,000 | 5 | 38 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0015-jf | 200,000 | 9 | 49.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0015-jf | 200,000 | 5 | 50.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0015-jf | 500,000 | 9 | 70.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0015-jf | 500,000 | 5 | 68.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0015-jf | 1,000,000 | 9 | 85.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0015-jf | 1,000,000 | 5 | 82 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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