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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(goe242-il) GOE 242 (MVA PR.2) AIRFOIL | Gottingen 242 (MVA PR.2) airfoil Max thickness 16.2% at 29.6% chord Max camber 7.5% at 49.7% chord | Remove Airfoil details Airfoil plotter |
(naca4415-il) NACA 4415 | NACA 4415 airfoil Max thickness 15% at 30.9% chord Max camber 4% at 40.2% chord | Remove Airfoil details Airfoil plotter |
(goe645-il) GOE 645 AIRFOIL | Gottingen 645 airfoil Max thickness 15.4% at 19.4% chord Max camber 4.8% at 39.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe242-il,naca4415-il,goe645-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe242-il | 50,000 | 9 | 6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe242-il | 50,000 | 5 | 20.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe242-il | 100,000 | 9 | 46.8 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe242-il | 100,000 | 5 | 54.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe242-il | 200,000 | 9 | 78.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe242-il | 200,000 | 5 | 80.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe242-il | 500,000 | 9 | 116.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe242-il | 500,000 | 5 | 114.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe242-il | 1,000,000 | 9 | 146.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe242-il | 1,000,000 | 5 | 137.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 50,000 | 9 | 7.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 50,000 | 5 | 27.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 100,000 | 9 | 48.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 100,000 | 5 | 50.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 200,000 | 9 | 71.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 200,000 | 5 | 68.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 500,000 | 9 | 97 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 500,000 | 5 | 90.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 1,000,000 | 9 | 119.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 1,000,000 | 5 | 109.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 50,000 | 9 | 9.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 50,000 | 5 | 28.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 100,000 | 9 | 43.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 100,000 | 5 | 48.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 200,000 | 9 | 66.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 200,000 | 5 | 65.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 500,000 | 9 | 93.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 500,000 | 5 | 84.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 1,000,000 | 9 | 110.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 1,000,000 | 5 | 88.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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