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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(goe559-il) GOE 559 AIRFOIL | Gottingen 559 airfoil Max thickness 11.2% at 30% chord Max camber 3.4% at 30% chord | Remove Airfoil details Airfoil plotter |
(m19-il) NACA M19 AIRFOIL | NACA/Munk M-19 airfoil Max thickness 6.2% at 30% chord Max camber 6% at 30% chord | Remove Airfoil details Airfoil plotter |
(p51dtip-il) P-51D TIP (BL215) AIRFOIL | P-51D tip (BL215) airfoil Max thickness 11.4% at 46.3% chord Max camber 1.3% at 46.3% chord | Remove Airfoil details Airfoil plotter |
(e398-il) EPPLER 398 AIRFOIL | Eppler E398 human powered aircraft airfoil Max thickness 14.2% at 29.6% chord Max camber 5.3% at 50.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe559-il,m19-il,p51dtip-il,e398-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe559-il | 50,000 | 9 | 30.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 50,000 | 5 | 28.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe559-il | 100,000 | 9 | 40.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 100,000 | 5 | 38.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe559-il | 200,000 | 9 | 50.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 200,000 | 5 | 50 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe559-il | 500,000 | 9 | 66.3 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 500,000 | 5 | 64.2 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe559-il | 1,000,000 | 9 | 76.8 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 1,000,000 | 5 | 74.2 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 50,000 | 9 | 20.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 50,000 | 5 | 37.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 100,000 | 9 | 57.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 100,000 | 5 | 57.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 200,000 | 9 | 77.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 200,000 | 5 | 75.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 500,000 | 9 | 102.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 500,000 | 5 | 83 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 1,000,000 | 9 | 117.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 1,000,000 | 5 | 92.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 50,000 | 9 | 22.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 50,000 | 5 | 23.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 100,000 | 9 | 40.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 100,000 | 5 | 35.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 200,000 | 9 | 54.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 200,000 | 5 | 49.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 500,000 | 9 | 74.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 500,000 | 5 | 63.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 1,000,000 | 9 | 89.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 1,000,000 | 5 | 68.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 50,000 | 9 | 6.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 50,000 | 5 | 17.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 100,000 | 9 | 47.5 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 100,000 | 5 | 54.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 200,000 | 9 | 84.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 200,000 | 5 | 86.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 500,000 | 9 | 129 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 500,000 | 5 | 124.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 1,000,000 | 9 | 163.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 1,000,000 | 5 | 147 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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