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 | ||
(goe572-il) GOE 572 AIRFOIL | Gottingen 572 airfoil Max thickness 18.6% at 29.9% chord Max camber 8.3% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(naca634421-il) NACA 63(4)-421 | NACA 63(4)-421 airfoil Max thickness 21% at 34.8% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe308-il) GOE 308 (MVA H.40) AIRFOIL | Gottingen 308 (MVA H.40) airfoil Max thickness 8.1% at 29.9% chord Max camber 5% at 29.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe572-il,naca634421-il,goe308-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe572-il | 50,000 | 9 | 3.1 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe572-il | 50,000 | 5 | 14.6 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe572-il | 100,000 | 9 | 29.9 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe572-il | 100,000 | 5 | 38.4 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe572-il | 200,000 | 9 | 55.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe572-il | 200,000 | 5 | 54.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe572-il | 500,000 | 9 | 79.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe572-il | 500,000 | 5 | 77.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe572-il | 1,000,000 | 9 | 103.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe572-il | 1,000,000 | 5 | 98.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca634421-il | 50,000 | 9 | 3.8 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634421-il | 50,000 | 5 | 9.4 at α=14.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca634421-il | 100,000 | 9 | 24.4 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634421-il | 100,000 | 5 | 35 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca634421-il | 200,000 | 9 | 61.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634421-il | 200,000 | 5 | 63 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca634421-il | 500,000 | 9 | 95.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634421-il | 500,000 | 5 | 90.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca634421-il | 1,000,000 | 9 | 119.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634421-il | 1,000,000 | 5 | 109.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe308-il | 50,000 | 9 | 32.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe308-il | 50,000 | 5 | 37.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe308-il | 100,000 | 9 | 54.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe308-il | 100,000 | 5 | 55.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe308-il | 200,000 | 9 | 74.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe308-il | 200,000 | 5 | 74.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe308-il | 500,000 | 9 | 103 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe308-il | 500,000 | 5 | 100.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe308-il | 1,000,000 | 9 | 126.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe308-il | 1,000,000 | 5 | 115.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||