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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(joukowsk0009-jf) Joukovsky f=0% t=9% | Joukowski 9% symmetrical airfoil Max thickness 9% at 25.5% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (joukowsk0009-jf)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| joukowsk0009-jf | 50,000 | 9 | 23.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0009-jf | 50,000 | 5 | 25.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0009-jf | 100,000 | 9 | 33.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0009-jf | 100,000 | 5 | 34.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0009-jf | 200,000 | 9 | 44.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0009-jf | 200,000 | 5 | 44.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0009-jf | 500,000 | 9 | 58.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0009-jf | 500,000 | 5 | 60.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0009-jf | 1,000,000 | 9 | 72.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0009-jf | 1,000,000 | 5 | 74.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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