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 | ||
(goe711-il) GOE 711 AIRFOIL | Gottingen 711 airfoil Max thickness 14.9% at 30% chord Max camber 6.3% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe481a-il) GOE 481A AIRFOIL | Gottingen 481A airfoil Max thickness 15.3% at 29.4% chord Max camber 5.5% at 39.4% chord | Remove Airfoil details Airfoil plotter |
(goe422-il) GOE 422 AIRFOIL | Gottingen 422 airfoil Max thickness 17.1% at 29.5% chord Max camber 6.5% at 39.5% chord | Remove Airfoil details Airfoil plotter |
(goe423-il) GOE 423 AIRFOIL | Gottingen 423 airfoil Max thickness 16.9% at 39.7% chord Max camber 5.1% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(goe134-il) GOE 134 (MVA H.12) AIRFOIL | Gottingen 134 (MVA H.12) airfoil Max thickness 9.5% at 30% chord Max camber 4% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe711-il,goe481a-il,goe422-il,goe423-il,goe134-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe711-il | 50,000 | 9 | 20.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe711-il | 50,000 | 5 | 33.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe711-il | 100,000 | 9 | 48.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe711-il | 100,000 | 5 | 49.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe711-il | 200,000 | 9 | 64.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe711-il | 200,000 | 5 | 62.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe711-il | 500,000 | 9 | 86.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe711-il | 500,000 | 5 | 83.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe711-il | 1,000,000 | 9 | 107.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe711-il | 1,000,000 | 5 | 102.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481a-il | 50,000 | 9 | 6.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481a-il | 50,000 | 5 | 27.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481a-il | 100,000 | 9 | 47.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481a-il | 100,000 | 5 | 46.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481a-il | 200,000 | 9 | 63.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481a-il | 200,000 | 5 | 59 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481a-il | 500,000 | 9 | 80.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481a-il | 500,000 | 5 | 74.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481a-il | 1,000,000 | 9 | 95.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481a-il | 1,000,000 | 5 | 81.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe422-il | 50,000 | 9 | 5.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe422-il | 50,000 | 5 | 19.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe422-il | 100,000 | 9 | 44.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe422-il | 100,000 | 5 | 47.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe422-il | 200,000 | 9 | 71 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe422-il | 200,000 | 5 | 66.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe422-il | 500,000 | 9 | 97.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe422-il | 500,000 | 5 | 85.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe422-il | 1,000,000 | 9 | 117.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe422-il | 1,000,000 | 5 | 98.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 50,000 | 9 | 4.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 50,000 | 5 | 14.4 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 100,000 | 9 | 22.8 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 100,000 | 5 | 40.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 200,000 | 9 | 69.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 200,000 | 5 | 70.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 500,000 | 9 | 105.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 500,000 | 5 | 101.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 1,000,000 | 9 | 133.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 1,000,000 | 5 | 124.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 50,000 | 9 | 29.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 50,000 | 5 | 38.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 100,000 | 9 | 50.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 100,000 | 5 | 55.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 200,000 | 9 | 70.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 200,000 | 5 | 71.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 500,000 | 9 | 96.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 500,000 | 5 | 93.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 1,000,000 | 9 | 114.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 1,000,000 | 5 | 109.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||