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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(goe395-il) GOE 395 AIRFOIL | Gottingen 395 airfoil Max thickness 6.1% at 19.9% chord Max camber 7% at 49.9% chord | Remove Airfoil details Airfoil plotter |
(naca651212-il) NACA 65(1)-212 | NACA 65(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe395-il,naca651212-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe395-il | 50,000 | 9 | 42.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe395-il | 50,000 | 5 | 43.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe395-il | 100,000 | 9 | 70.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe395-il | 100,000 | 5 | 71 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe395-il | 200,000 | 9 | 102.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe395-il | 200,000 | 5 | 100.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe395-il | 500,000 | 9 | 149.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe395-il | 500,000 | 5 | 117.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe395-il | 1,000,000 | 9 | 157.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe395-il | 1,000,000 | 5 | 124.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212-il | 50,000 | 9 | 26.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212-il | 50,000 | 5 | 28.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212-il | 100,000 | 9 | 46.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212-il | 100,000 | 5 | 42.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212-il | 200,000 | 9 | 55.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212-il | 200,000 | 5 | 52.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212-il | 500,000 | 9 | 76.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212-il | 500,000 | 5 | 66.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212-il | 1,000,000 | 9 | 87.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212-il | 1,000,000 | 5 | 70.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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