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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(goe628-il) GOE 628 AIRFOIL | Gottingen 628 airfoil Max thickness 16.7% at 19.4% chord Max camber 5.6% at 39.3% chord | Remove Airfoil details Airfoil plotter |
(e521-il) EPPLER 521 AIRFOIL | Eppler E521 tailplane airfoil Max thickness 13.8% at 37% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe623-il) GOE 623 AIRFOIL | Gottingen 623 airfoil Max thickness 12% at 30% chord Max camber 3.8% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe628-il,e521-il,goe623-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe628-il | 50,000 | 9 | 6.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe628-il | 50,000 | 5 | 27.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe628-il | 100,000 | 9 | 43.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe628-il | 100,000 | 5 | 47.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe628-il | 200,000 | 9 | 64.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe628-il | 200,000 | 5 | 63.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe628-il | 500,000 | 9 | 88.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe628-il | 500,000 | 5 | 84.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe628-il | 1,000,000 | 9 | 111.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe628-il | 1,000,000 | 5 | 107.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 50,000 | 9 | 29.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 50,000 | 5 | 29.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 100,000 | 9 | 43.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 100,000 | 5 | 34.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 200,000 | 9 | 44.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 200,000 | 5 | 43.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 500,000 | 9 | 58.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 500,000 | 5 | 56.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 1,000,000 | 9 | 70 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 1,000,000 | 5 | 66.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe623-il | 50,000 | 9 | 27.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 50,000 | 5 | 36 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe623-il | 100,000 | 9 | 53.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 100,000 | 5 | 55 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe623-il | 200,000 | 9 | 75.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 200,000 | 5 | 72.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe623-il | 500,000 | 9 | 102.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 500,000 | 5 | 91.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe623-il | 1,000,000 | 9 | 120.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 1,000,000 | 5 | 104.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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