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 | ||
(goe368-il) GOE 368 AIRFOIL | Gottingen 368 airfoil Max thickness 7.7% at 14.9% chord Max camber 3.8% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(naca633018-il) NACA 63(3)-018 | NACA 63(3)-018 airfoil Max thickness 18% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe264-il) GOE 264 AIRFOIL | Gottingen 264 airfoil Max thickness 6.4% at 20.2% chord Max camber 5.7% at 28.9% chord | Remove Airfoil details Airfoil plotter |
(goe330-il) GOE 330 (PFALZ 59) AIRFOIL | Gottingen 330 (Pfalz 59) airfoil Max thickness 10.2% at 29.9% chord Max camber 5.8% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(naca6412-il) NACA 6412 | NACA 6412 airfoil Max thickness 12% at 30.1% chord Max camber 6% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(goe385-il) GOE 385 AIRFOIL | Gottingen 385 airfoil Max thickness 9.9% at 29.9% chord Max camber 4.1% at 29.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe368-il,naca633018-il,goe264-il,goe330-il,naca6412-il,goe385-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe368-il | 50,000 | 9 | 29.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe368-il | 50,000 | 5 | 36 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe368-il | 100,000 | 9 | 49.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe368-il | 100,000 | 5 | 50.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe368-il | 200,000 | 9 | 64.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe368-il | 200,000 | 5 | 63.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe368-il | 500,000 | 9 | 83.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe368-il | 500,000 | 5 | 83.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe368-il | 1,000,000 | 9 | 98.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe368-il | 1,000,000 | 5 | 98.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 50,000 | 9 | 23.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 50,000 | 5 | 20.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 100,000 | 9 | 40.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 100,000 | 5 | 36.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 200,000 | 9 | 53.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 200,000 | 5 | 50.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 500,000 | 9 | 73 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 500,000 | 5 | 61.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 1,000,000 | 9 | 83 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 1,000,000 | 5 | 65.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe264-il | 50,000 | 9 | 32.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe264-il | 50,000 | 5 | 41.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe264-il | 100,000 | 9 | 59.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe264-il | 100,000 | 5 | 60.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe264-il | 200,000 | 9 | 79.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe264-il | 200,000 | 5 | 79.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe264-il | 500,000 | 9 | 106.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe264-il | 500,000 | 5 | 104.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe264-il | 1,000,000 | 9 | 126.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe264-il | 1,000,000 | 5 | 121.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe330-il | 50,000 | 9 | 24.8 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe330-il | 50,000 | 5 | 38.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe330-il | 100,000 | 9 | 56.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe330-il | 100,000 | 5 | 58.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe330-il | 200,000 | 9 | 78.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe330-il | 200,000 | 5 | 75.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe330-il | 500,000 | 9 | 103.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe330-il | 500,000 | 5 | 101.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe330-il | 1,000,000 | 9 | 128.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe330-il | 1,000,000 | 5 | 121.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca6412-il | 50,000 | 9 | 9.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca6412-il | 50,000 | 5 | 29.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca6412-il | 100,000 | 9 | 53.1 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca6412-il | 100,000 | 5 | 58.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca6412-il | 200,000 | 9 | 80 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca6412-il | 200,000 | 5 | 81.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca6412-il | 500,000 | 9 | 114.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca6412-il | 500,000 | 5 | 111.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca6412-il | 1,000,000 | 9 | 142.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca6412-il | 1,000,000 | 5 | 136.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe385-il | 50,000 | 9 | 29.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe385-il | 50,000 | 5 | 37.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe385-il | 100,000 | 9 | 51.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe385-il | 100,000 | 5 | 56.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe385-il | 200,000 | 9 | 73 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe385-il | 200,000 | 5 | 72.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe385-il | 500,000 | 9 | 97.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe385-il | 500,000 | 5 | 93.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe385-il | 1,000,000 | 9 | 115.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe385-il | 1,000,000 | 5 | 108.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||