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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(goe625-il) GOE 625 AIRFOIL | Gottingen 625 airfoil Max thickness 20% at 30% chord Max camber 6.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe614-il) GOE 614 AIRFOIL | Gottingen 614 airfoil Max thickness 18.8% at 29.2% chord Max camber 6.2% at 39.2% chord | Remove Airfoil details Airfoil plotter |
(s8037-il) S8037 (16%) | Selig S8037 low Reynolds number airfoil Max thickness 16% at 33.5% chord Max camber 1.9% at 40.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe625-il,goe614-il,s8037-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe625-il | 50,000 | 9 | 3.8 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe625-il | 50,000 | 5 | 18.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe625-il | 100,000 | 9 | 33.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe625-il | 100,000 | 5 | 42.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe625-il | 200,000 | 9 | 58.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe625-il | 200,000 | 5 | 57.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe625-il | 500,000 | 9 | 80.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe625-il | 500,000 | 5 | 77.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe625-il | 1,000,000 | 9 | 101.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe625-il | 1,000,000 | 5 | 99.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe614-il | 50,000 | 9 | 3.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 50,000 | 5 | 16.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe614-il | 100,000 | 9 | 33.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 100,000 | 5 | 43.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe614-il | 200,000 | 9 | 63.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 200,000 | 5 | 59.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe614-il | 500,000 | 9 | 84.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 500,000 | 5 | 77.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe614-il | 1,000,000 | 9 | 105.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 1,000,000 | 5 | 79.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8037-il | 50,000 | 9 | 7.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8037-il | 50,000 | 5 | 22.8 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8037-il | 100,000 | 9 | 47 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8037-il | 100,000 | 5 | 48.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8037-il | 200,000 | 9 | 71.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8037-il | 200,000 | 5 | 69 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8037-il | 500,000 | 9 | 99.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8037-il | 500,000 | 5 | 85.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8037-il | 1,000,000 | 9 | 110.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8037-il | 1,000,000 | 5 | 98.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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