Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(goe518-il) GOE 518 AIRFOIL | Gottingen 518 airfoil Max thickness 18% at 29.8% chord Max camber 7.3% at 29.8% chord | Remove Airfoil details Airfoil plotter |
(goe410-il) GOE 410 AIRFOIL | Gottingen 410 airfoil Max thickness 16.1% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe530-il) GOE 530 AIRFOIL | Gottingen 530 airfoil Max thickness 12.9% at 29.8% chord Max camber 5.1% at 29.8% chord | Remove Airfoil details Airfoil plotter |
(goe402-il) GOE 402 AIRFOIL | Gottingen 402 airfoil Max thickness 6.8% at 20% chord Max camber 5.7% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe518-il,goe410-il,goe530-il,goe402-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe518-il | 50,000 | 9 | 6.5 at α=-3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe518-il | 50,000 | 5 | 23.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe518-il | 100,000 | 9 | 41.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe518-il | 100,000 | 5 | 39.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe518-il | 200,000 | 9 | 54.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe518-il | 200,000 | 5 | 48.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe518-il | 500,000 | 9 | 64.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe518-il | 500,000 | 5 | 61.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe518-il | 1,000,000 | 9 | 81 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe518-il | 1,000,000 | 5 | 79.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe410-il | 50,000 | 9 | 20.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe410-il | 50,000 | 5 | 25.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe410-il | 100,000 | 9 | 37.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe410-il | 100,000 | 5 | 35.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe410-il | 200,000 | 9 | 46.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe410-il | 200,000 | 5 | 45.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe410-il | 500,000 | 9 | 62.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe410-il | 500,000 | 5 | 65.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe410-il | 1,000,000 | 9 | 82 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe410-il | 1,000,000 | 5 | 81.8 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe530-il | 50,000 | 9 | 14 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe530-il | 50,000 | 5 | 32.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe530-il | 100,000 | 9 | 49.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe530-il | 100,000 | 5 | 50.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe530-il | 200,000 | 9 | 69 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe530-il | 200,000 | 5 | 66.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe530-il | 500,000 | 9 | 94.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe530-il | 500,000 | 5 | 89.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe530-il | 1,000,000 | 9 | 115.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe530-il | 1,000,000 | 5 | 101.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe402-il | 50,000 | 9 | 31.5 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe402-il | 50,000 | 5 | 40.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe402-il | 100,000 | 9 | 55.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe402-il | 100,000 | 5 | 59.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe402-il | 200,000 | 9 | 75.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe402-il | 200,000 | 5 | 77.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe402-il | 500,000 | 9 | 105.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe402-il | 500,000 | 5 | 105.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe402-il | 1,000,000 | 9 | 129.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe402-il | 1,000,000 | 5 | 126.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||