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 | ||
(naca633618-il) NACA 63(3)-618 | NACA 63(3)-618 airfoil Max thickness 18% at 34.7% chord Max camber 3.3% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe164-il) GOE 164 (MVA MK.10) AIRFOIL | Gottingen 164 (MVA MK.10) airfoil Max thickness 8.9% at 19.9% chord Max camber 6.6% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe361-il) GOE 361 AIRFOIL | Gottingen 361 airfoil Max thickness 6.8% at 20% chord Max camber 5.5% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (naca633618-il,goe164-il,goe361-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca633618-il | 50,000 | 9 | 5.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633618-il | 50,000 | 5 | 14.2 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633618-il | 100,000 | 9 | 41.6 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633618-il | 100,000 | 5 | 46.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633618-il | 200,000 | 9 | 74 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633618-il | 200,000 | 5 | 73.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633618-il | 500,000 | 9 | 107.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633618-il | 500,000 | 5 | 102.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633618-il | 1,000,000 | 9 | 133.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633618-il | 1,000,000 | 5 | 122.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe164-il | 50,000 | 9 | 34.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe164-il | 50,000 | 5 | 43.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe164-il | 100,000 | 9 | 60.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe164-il | 100,000 | 5 | 62.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe164-il | 200,000 | 9 | 81.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe164-il | 200,000 | 5 | 77.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe164-il | 500,000 | 9 | 104.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe164-il | 500,000 | 5 | 92 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe164-il | 1,000,000 | 9 | 112.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe164-il | 1,000,000 | 5 | 102.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe361-il | 50,000 | 9 | 39.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe361-il | 50,000 | 5 | 42.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe361-il | 100,000 | 9 | 57.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe361-il | 100,000 | 5 | 59.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe361-il | 200,000 | 9 | 76.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe361-il | 200,000 | 5 | 77.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe361-il | 500,000 | 9 | 103.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe361-il | 500,000 | 5 | 101.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe361-il | 1,000,000 | 9 | 123.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe361-il | 1,000,000 | 5 | 119.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||