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 | ||
(goe440-il) GOE 440 AIRFOIL | Gottingen 440 airfoil Max thickness 15.3% at 30% chord Max camber 9.7% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe510-il) GOE 510 AIRFOIL | Gottingen 510 airfoil Max thickness 13.7% at 19.7% chord Max camber 5.8% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(goe506-il) GOE 506 AIRFOIL | Gottingen 506 airfoil Max thickness 16.5% at 29.3% chord Max camber 4.7% at 39.3% chord | Remove Airfoil details Airfoil plotter |
(goe508-il) GOE 508 AIRFOIL | Gottingen 508 airfoil Max thickness 16.5% at 30% chord Max camber 5.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe436-il) GOE 436 AIRFOIL | Gottingen 436 airfoil Max thickness 11% at 30% chord Max camber 3.8% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe440-il,goe510-il,goe506-il,goe508-il,goe436-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe440-il | 50,000 | 9 | 9.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 50,000 | 5 | 31.9 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 100,000 | 9 | 53.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 100,000 | 5 | 52.9 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 200,000 | 9 | 71.1 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 200,000 | 5 | 67.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 500,000 | 9 | 92.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 500,000 | 5 | 86.7 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 1,000,000 | 9 | 109.5 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 1,000,000 | 5 | 100.3 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 50,000 | 9 | 8.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 50,000 | 5 | 29.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 100,000 | 9 | 48.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 100,000 | 5 | 48.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 200,000 | 9 | 65.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 200,000 | 5 | 61.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 500,000 | 9 | 84.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 500,000 | 5 | 82.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 1,000,000 | 9 | 106.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 1,000,000 | 5 | 99.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe506-il | 50,000 | 9 | 10.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe506-il | 50,000 | 5 | 28 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe506-il | 100,000 | 9 | 45.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe506-il | 100,000 | 5 | 40.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe506-il | 200,000 | 9 | 58 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe506-il | 200,000 | 5 | 48.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe506-il | 500,000 | 9 | 64.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe506-il | 500,000 | 5 | 61.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe506-il | 1,000,000 | 9 | 81.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe506-il | 1,000,000 | 5 | 75.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe508-il | 50,000 | 9 | 5.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe508-il | 50,000 | 5 | 13.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe508-il | 100,000 | 9 | 40.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe508-il | 100,000 | 5 | 43.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe508-il | 200,000 | 9 | 71.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe508-il | 200,000 | 5 | 69.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe508-il | 500,000 | 9 | 105.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe508-il | 500,000 | 5 | 97.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe508-il | 1,000,000 | 9 | 132.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe508-il | 1,000,000 | 5 | 115.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe436-il | 50,000 | 9 | 23.5 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 50,000 | 5 | 34.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe436-il | 100,000 | 9 | 47.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 100,000 | 5 | 51.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe436-il | 200,000 | 9 | 68.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 200,000 | 5 | 69.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe436-il | 500,000 | 9 | 96.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 500,000 | 5 | 92.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe436-il | 1,000,000 | 9 | 118.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 1,000,000 | 5 | 108.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||