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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(ag18-il) AG18 | Drela AG18 airfoil Max thickness 5.9% at 20.7% chord Max camber 2.2% at 44.1% chord | Remove Airfoil details Airfoil plotter |
(goe704-il) GOE 704 AIRFOIL | Gottingen 704 airfoil Max thickness 12.9% at 29.9% chord Max camber 2.1% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe535-il) GOE 535 AIRFOIL | Gottingen 535 airfoil Max thickness 16.1% at 20% chord Max camber 5.8% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag18-il,goe704-il,goe535-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag18-il | 50,000 | 9 | 35.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 50,000 | 5 | 36.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 100,000 | 9 | 50.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 100,000 | 5 | 48.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 200,000 | 9 | 65.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 200,000 | 5 | 60.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 500,000 | 9 | 81.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 500,000 | 5 | 77 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 1,000,000 | 9 | 95.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 1,000,000 | 5 | 90.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe704-il | 50,000 | 9 | 26 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe704-il | 50,000 | 5 | 31.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe704-il | 100,000 | 9 | 44.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe704-il | 100,000 | 5 | 44.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe704-il | 200,000 | 9 | 57.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe704-il | 200,000 | 5 | 57.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe704-il | 500,000 | 9 | 78.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe704-il | 500,000 | 5 | 72.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe704-il | 1,000,000 | 9 | 90.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe704-il | 1,000,000 | 5 | 83 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe535-il | 50,000 | 9 | 7.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe535-il | 50,000 | 5 | 29.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe535-il | 100,000 | 9 | 43.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe535-il | 100,000 | 5 | 50.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe535-il | 200,000 | 9 | 68.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe535-il | 200,000 | 5 | 68.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe535-il | 500,000 | 9 | 96.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe535-il | 500,000 | 5 | 90.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe535-il | 1,000,000 | 9 | 116.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe535-il | 1,000,000 | 5 | 110.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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