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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(goe124-il) GOE 124 (MVA H.4) AIRFOIL | Gottingen 124 (MVA H.4) airfoil Max thickness 7.9% at 29.9% chord Max camber 5.6% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe502-il) GOE 502 AIRFOIL | Gottingen 502 airfoil Max thickness 15.9% at 29.3% chord Max camber 6.1% at 49.4% chord | Remove Airfoil details Airfoil plotter |
(e420-il) EPPLER 420 AIRFOIL | Eppler E420 high lift airfoil Max thickness 14.3% at 22.8% chord Max camber 10.6% at 40.5% chord | Remove Airfoil details Airfoil plotter |
(raf32md-il) RAF 32 MOD AIRFOIL | RAF-32 MOD airfoil Max thickness 10.2% at 30% chord Max camber 4% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe124-il,goe502-il,e420-il,raf32md-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe124-il | 50,000 | 9 | 35.9 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe124-il | 50,000 | 5 | 41.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe124-il | 100,000 | 9 | 60.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe124-il | 100,000 | 5 | 63.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe124-il | 200,000 | 9 | 84.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe124-il | 200,000 | 5 | 83.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe124-il | 500,000 | 9 | 114.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe124-il | 500,000 | 5 | 107.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe124-il | 1,000,000 | 9 | 133.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe124-il | 1,000,000 | 5 | 126.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe502-il | 50,000 | 9 | 5.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 50,000 | 5 | 18.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe502-il | 100,000 | 9 | 42.1 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 100,000 | 5 | 53 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe502-il | 200,000 | 9 | 76 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 200,000 | 5 | 75.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe502-il | 500,000 | 9 | 106.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 500,000 | 5 | 100.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe502-il | 1,000,000 | 9 | 132.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 1,000,000 | 5 | 112.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e420-il | 50,000 | 9 | 5.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 50,000 | 5 | 13.3 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e420-il | 100,000 | 9 | 20 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 100,000 | 5 | 47.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e420-il | 200,000 | 9 | 63.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 200,000 | 5 | 75.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e420-il | 500,000 | 9 | 107.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 500,000 | 5 | 106.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e420-il | 1,000,000 | 9 | 137.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 1,000,000 | 5 | 134.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 50,000 | 9 | 38 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 50,000 | 5 | 37.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 100,000 | 9 | 62.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 100,000 | 5 | 61.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 200,000 | 9 | 87.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 200,000 | 5 | 83.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 500,000 | 9 | 120.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 500,000 | 5 | 110.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 1,000,000 | 9 | 144.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 1,000,000 | 5 | 124.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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