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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(goe238-il) GOE 238 (HANSA-BRANDENBURG) AIRFOIL | Gottingen 238 (HANSA-BRANDENBURG) airfoil Max thickness 9.8% at 29.8% chord Max camber 5.5% at 29.8% chord | Remove Airfoil details Airfoil plotter |
(goe746-il) GOE 746 AIRFOIL | Gottingen 746 airfoil Max thickness 9.8% at 30% chord Max camber 5% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe63-il) GOE 63 AIRFOIL | Gottingen 63 airfoil Max thickness 8.3% at 19.9% chord Max camber 6.7% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(naca16015-il) NACA 16-015 | NACA 16-015 airfoil Max thickness 15% at 50% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(fx72150a-il) WORTMANN FX 72-MS-150A AIRFOIL | Wortmann FX 72-MS-150A airfoil Max thickness 15% at 37.1% chord Max camber 8.3% at 46.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe238-il,goe746-il,goe63-il,naca16015-il,fx72150a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe238-il | 50,000 | 9 | 9.8 at α=-3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe238-il | 50,000 | 5 | 24.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe238-il | 100,000 | 9 | 51.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe238-il | 100,000 | 5 | 55.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe238-il | 200,000 | 9 | 80.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe238-il | 200,000 | 5 | 80.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe238-il | 500,000 | 9 | 117.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe238-il | 500,000 | 5 | 110 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe238-il | 1,000,000 | 9 | 143.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe238-il | 1,000,000 | 5 | 130.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe746-il | 50,000 | 9 | 7.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 50,000 | 5 | 20.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe746-il | 100,000 | 9 | 46.3 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 100,000 | 5 | 49.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe746-il | 200,000 | 9 | 73.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 200,000 | 5 | 73.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe746-il | 500,000 | 9 | 106.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 500,000 | 5 | 102.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe746-il | 1,000,000 | 9 | 129.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 1,000,000 | 5 | 118.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe63-il | 50,000 | 9 | 30.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe63-il | 50,000 | 5 | 41.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe63-il | 100,000 | 9 | 61 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe63-il | 100,000 | 5 | 63.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe63-il | 200,000 | 9 | 86.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe63-il | 200,000 | 5 | 80.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe63-il | 500,000 | 9 | 110.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe63-il | 500,000 | 5 | 102.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe63-il | 1,000,000 | 9 | 128.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe63-il | 1,000,000 | 5 | 121.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 50,000 | 9 | 22.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 50,000 | 5 | 21.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 100,000 | 9 | 29.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 100,000 | 5 | 28.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 200,000 | 9 | 40.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 200,000 | 5 | 32 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 500,000 | 9 | 44.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 500,000 | 5 | 39.7 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 1,000,000 | 9 | 50.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 1,000,000 | 5 | 50.5 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150a-il | 50,000 | 9 | 6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 50,000 | 5 | 10.4 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150a-il | 100,000 | 9 | 13.2 at α=15.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 100,000 | 5 | 40.5 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150a-il | 200,000 | 9 | 58.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 200,000 | 5 | 78.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150a-il | 500,000 | 9 | 123.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 500,000 | 5 | 121.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150a-il | 1,000,000 | 9 | 160.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 1,000,000 | 5 | 154 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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