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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(fx66182-il) FX 66-182 AIRFOIL | Wortmann FX 66-182 airfoil Max thickness 18.2% at 33.9% chord Max camber 3.8% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(goe290-il) GOE 290 (MVA 290) AIRFOIL | Gottingen 290 (MVA 290) airfoil Max thickness 17.6% at 29.1% chord Max camber 3.9% at 39.2% chord | Remove Airfoil details Airfoil plotter |
(goe679-il) GOE 679 AIRFOIL | Gottingen 679 airfoil Max thickness 18.3% at 29.1% chord Max camber 4.5% at 39.1% chord | Remove Airfoil details Airfoil plotter |
(s1012-il) S1012 | Selig S1012 HPV airfoil Max thickness 12% at 37.3% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx66182-il,goe290-il,goe679-il,s1012-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx66182-il | 50,000 | 9 | 4.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 50,000 | 5 | 8.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66182-il | 100,000 | 9 | 5.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 100,000 | 5 | 30.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66182-il | 200,000 | 9 | 61.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 200,000 | 5 | 67.9 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66182-il | 500,000 | 9 | 107.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 500,000 | 5 | 104.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66182-il | 1,000,000 | 9 | 134.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 1,000,000 | 5 | 128.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe290-il | 50,000 | 9 | 6.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 50,000 | 5 | 22.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe290-il | 100,000 | 9 | 41.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 100,000 | 5 | 46.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe290-il | 200,000 | 9 | 69 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 200,000 | 5 | 67 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe290-il | 500,000 | 9 | 96.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 500,000 | 5 | 84 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe290-il | 1,000,000 | 9 | 112.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 1,000,000 | 5 | 92.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe679-il | 50,000 | 9 | 5.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 50,000 | 5 | 25.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe679-il | 100,000 | 9 | 42.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 100,000 | 5 | 41.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe679-il | 200,000 | 9 | 58.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 200,000 | 5 | 54.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe679-il | 500,000 | 9 | 76.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 500,000 | 5 | 72.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe679-il | 1,000,000 | 9 | 95.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 1,000,000 | 5 | 88.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1012-il | 50,000 | 9 | 26.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 50,000 | 5 | 25.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1012-il | 100,000 | 9 | 37.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 100,000 | 5 | 31.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1012-il | 200,000 | 9 | 37.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 200,000 | 5 | 40 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1012-il | 500,000 | 9 | 53.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 500,000 | 5 | 56.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1012-il | 1,000,000 | 9 | 69.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 1,000,000 | 5 | 70.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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