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 | ||
(goe534-il) GOE 534 AIRFOIL | Gottingen 534 airfoil Max thickness 14.1% at 19.6% chord Max camber 5.2% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(goe704-il) GOE 704 AIRFOIL | Gottingen 704 airfoil Max thickness 12.9% at 29.9% chord Max camber 2.1% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe358-il) GOE 358 AIRFOIL | Gottingen 358 airfoil Max thickness 10.9% at 20% chord Max camber 5.6% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe534-il,goe704-il,goe358-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe534-il | 50,000 | 9 | 20 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe534-il | 50,000 | 5 | 32.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe534-il | 100,000 | 9 | 44 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe534-il | 100,000 | 5 | 50.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe534-il | 200,000 | 9 | 65.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe534-il | 200,000 | 5 | 67.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe534-il | 500,000 | 9 | 93.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe534-il | 500,000 | 5 | 91 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe534-il | 1,000,000 | 9 | 114.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe534-il | 1,000,000 | 5 | 110.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe704-il | 50,000 | 9 | 26 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe704-il | 50,000 | 5 | 31.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe704-il | 100,000 | 9 | 44.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe704-il | 100,000 | 5 | 44.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe704-il | 200,000 | 9 | 57.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe704-il | 200,000 | 5 | 57.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe704-il | 500,000 | 9 | 78.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe704-il | 500,000 | 5 | 72.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe704-il | 1,000,000 | 9 | 90.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe704-il | 1,000,000 | 5 | 83 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 50,000 | 9 | 37.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 50,000 | 5 | 42.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 100,000 | 9 | 58.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 100,000 | 5 | 61.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 200,000 | 9 | 79 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 200,000 | 5 | 79 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 500,000 | 9 | 105.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 500,000 | 5 | 99.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 1,000,000 | 9 | 119.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 1,000,000 | 5 | 115.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||