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 | ||
(goe681-il) GOE 681 AIRFOIL | Gottingen 681 airfoil Max thickness 16.8% at 29.2% chord Max camber 4.4% at 39.2% chord | Remove Airfoil details Airfoil plotter |
(goe702-il) GOE 702 AIRFOIL | Gottingen 702 airfoil Max thickness 16.6% at 19.4% chord Max camber 5.1% at 39.4% chord | Remove Airfoil details Airfoil plotter |
(goe587-il) GOE 587 AIRFOIL | Gottingen 587 airfoil Max thickness 5.8% at 40% chord Max camber 3% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe703-il) GOE 703 AIRFOIL | Gottingen 703 airfoil Max thickness 19.4% at 30% chord Max camber 2.3% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe681-il,goe702-il,goe587-il,goe703-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe681-il | 50,000 | 9 | 9.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 50,000 | 5 | 26.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe681-il | 100,000 | 9 | 44.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 100,000 | 5 | 42.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe681-il | 200,000 | 9 | 61.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 200,000 | 5 | 55.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe681-il | 500,000 | 9 | 79.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 500,000 | 5 | 73.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe681-il | 1,000,000 | 9 | 97.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 1,000,000 | 5 | 94 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe702-il | 50,000 | 9 | 4.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 50,000 | 5 | 20.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe702-il | 100,000 | 9 | 32 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 100,000 | 5 | 43.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe702-il | 200,000 | 9 | 57.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 200,000 | 5 | 61.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe702-il | 500,000 | 9 | 88.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 500,000 | 5 | 89.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe702-il | 1,000,000 | 9 | 117.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 1,000,000 | 5 | 116.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe587-il | 50,000 | 9 | 36.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 50,000 | 5 | 37 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe587-il | 100,000 | 9 | 50.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 100,000 | 5 | 50.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe587-il | 200,000 | 9 | 63.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 200,000 | 5 | 62.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe587-il | 500,000 | 9 | 77.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 500,000 | 5 | 70.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe587-il | 1,000,000 | 9 | 77.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 1,000,000 | 5 | 77.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe703-il | 50,000 | 9 | 5.5 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 50,000 | 5 | 22.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe703-il | 100,000 | 9 | 40 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 100,000 | 5 | 43 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe703-il | 200,000 | 9 | 63.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 200,000 | 5 | 49.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe703-il | 500,000 | 9 | 67 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 500,000 | 5 | 57.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe703-il | 1,000,000 | 9 | 75.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 1,000,000 | 5 | 65.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||