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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(joukowsk0018-jf) Joukovsky f=0% t=18% | Joukowski 18% symmetrical airfoil Max thickness 18% at 27.1% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (joukowsk0018-jf)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| joukowsk0018-jf | 50,000 | 9 | 14.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0018-jf | 50,000 | 5 | 23 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0018-jf | 100,000 | 9 | 34.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0018-jf | 100,000 | 5 | 36.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0018-jf | 200,000 | 9 | 49.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0018-jf | 200,000 | 5 | 49.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0018-jf | 500,000 | 9 | 70.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0018-jf | 500,000 | 5 | 67.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0018-jf | 1,000,000 | 9 | 86.4 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0018-jf | 1,000,000 | 5 | 81 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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