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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(s4053-il) S4053 | Selig S4053 low Reynolds number airfoil Max thickness 8.9% at 30.9% chord Max camber 3% at 45% chord | Remove Airfoil details Airfoil plotter |
(goe515-il) GOE 515 AIRFOIL | Gottingen 515 airfoil Max thickness 8.5% at 30% chord Max camber 2.8% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe121-il) GOE 121 (MVA H.1) AIRFOIL | Gottingen 121 (MVA H.1) airfoil Max thickness 6.7% at 19.9% chord Max camber 4.6% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s4053-il,goe515-il,goe121-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s4053-il | 50,000 | 9 | 38.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4053-il | 50,000 | 5 | 39.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4053-il | 100,000 | 9 | 58.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4053-il | 100,000 | 5 | 57.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4053-il | 200,000 | 9 | 80.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4053-il | 200,000 | 5 | 75.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4053-il | 500,000 | 9 | 109.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4053-il | 500,000 | 5 | 96.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4053-il | 1,000,000 | 9 | 129 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4053-il | 1,000,000 | 5 | 109.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe515-il | 50,000 | 9 | 37.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe515-il | 50,000 | 5 | 37.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe515-il | 100,000 | 9 | 56.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe515-il | 100,000 | 5 | 54.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe515-il | 200,000 | 9 | 77.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe515-il | 200,000 | 5 | 71 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe515-il | 500,000 | 9 | 103.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe515-il | 500,000 | 5 | 88 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe515-il | 1,000,000 | 9 | 119 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe515-il | 1,000,000 | 5 | 95.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe121-il | 50,000 | 9 | 40.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe121-il | 50,000 | 5 | 43.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe121-il | 100,000 | 9 | 60.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe121-il | 100,000 | 5 | 59.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe121-il | 200,000 | 9 | 79.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe121-il | 200,000 | 5 | 74.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe121-il | 500,000 | 9 | 99.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe121-il | 500,000 | 5 | 87 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe121-il | 1,000,000 | 9 | 104.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe121-il | 1,000,000 | 5 | 97.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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