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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(goe366-il) GOE 366 AIRFOIL | Gottingen 366 airfoil Max thickness 13.1% at 29.8% chord Max camber 7.2% at 39.8% chord | Remove Airfoil details Airfoil plotter |
(naca644421-il) NACA 64(4)-421 | NACA 64(4)-421 airfoil Max thickness 20.9% at 34.8% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(e193-il) E193 (10.22%) | Eppler E193 low Reynolds number airfoil Max thickness 10.2% at 31% chord Max camber 3% at 44.7% chord | Remove Airfoil details Airfoil plotter |
(goe255-il) GOE 255 (MVA CA.6) AIRFOIL | Gottingen 255 (MVA CA.6) airfoil Max thickness 18.5% at 29.1% chord Max camber 4.8% at 49.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe366-il,naca644421-il,e193-il,goe255-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe366-il | 50,000 | 9 | 8.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe366-il | 50,000 | 5 | 30.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe366-il | 100,000 | 9 | 51.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe366-il | 100,000 | 5 | 55 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe366-il | 200,000 | 9 | 82.6 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe366-il | 200,000 | 5 | 73.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe366-il | 500,000 | 9 | 102.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe366-il | 500,000 | 5 | 97.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe366-il | 1,000,000 | 9 | 128.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe366-il | 1,000,000 | 5 | 121.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 50,000 | 9 | 3.9 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 50,000 | 5 | 11.3 at α=14.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 100,000 | 9 | 21.9 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 100,000 | 5 | 26.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 200,000 | 9 | 61.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 200,000 | 5 | 62.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 500,000 | 9 | 98.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 500,000 | 5 | 93.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 1,000,000 | 9 | 124.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 1,000,000 | 5 | 112.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e193-il | 50,000 | 9 | 35.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e193-il | 50,000 | 5 | 35.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e193-il | 100,000 | 9 | 58.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e193-il | 100,000 | 5 | 58.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e193-il | 200,000 | 9 | 82.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e193-il | 200,000 | 5 | 80.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e193-il | 500,000 | 9 | 114.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e193-il | 500,000 | 5 | 107.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e193-il | 1,000,000 | 9 | 138.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e193-il | 1,000,000 | 5 | 125.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 50,000 | 9 | 5.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 50,000 | 5 | 15.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 100,000 | 9 | 41.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 100,000 | 5 | 47.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 200,000 | 9 | 72.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 200,000 | 5 | 71.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 500,000 | 9 | 105.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 500,000 | 5 | 90.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 1,000,000 | 9 | 127.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 1,000,000 | 5 | 96.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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