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 | ||
(goe147-il) GOE 147 (MVA H.6) AIRFOIL | Gottingen 147 (MVA H.6) airfoil Max thickness 7.5% at 14.9% chord Max camber 3.8% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(ag37-il) AG37 | Drela AG37 airfoil Max thickness 7.7% at 26.5% chord Max camber 2.1% at 35.5% chord | Remove Airfoil details Airfoil plotter |
(ag35-il) AG35 | Drela AG35 airfoil Max thickness 8.7% at 27.9% chord Max camber 2.3% at 37% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe147-il,ag37-il,ag35-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe147-il | 50,000 | 9 | 29.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe147-il | 50,000 | 5 | 36.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe147-il | 100,000 | 9 | 48.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe147-il | 100,000 | 5 | 49.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe147-il | 200,000 | 9 | 64.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe147-il | 200,000 | 5 | 66.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe147-il | 500,000 | 9 | 86.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe147-il | 500,000 | 5 | 86.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe147-il | 1,000,000 | 9 | 102.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe147-il | 1,000,000 | 5 | 101.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag37-il | 50,000 | 9 | 32.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag37-il | 50,000 | 5 | 36.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag37-il | 100,000 | 9 | 49.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag37-il | 100,000 | 5 | 49.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag37-il | 200,000 | 9 | 65.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag37-il | 200,000 | 5 | 62.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag37-il | 500,000 | 9 | 85.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag37-il | 500,000 | 5 | 78.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag37-il | 1,000,000 | 9 | 98.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag37-il | 1,000,000 | 5 | 89.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag35-il | 50,000 | 9 | 32.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag35-il | 50,000 | 5 | 36.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag35-il | 100,000 | 9 | 50.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag35-il | 100,000 | 5 | 51.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag35-il | 200,000 | 9 | 68.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag35-il | 200,000 | 5 | 65.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag35-il | 500,000 | 9 | 90.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag35-il | 500,000 | 5 | 82.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag35-il | 1,000,000 | 9 | 105.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag35-il | 1,000,000 | 5 | 95.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||