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 | ||
(goe392-il) GOE 392 AIRFOIL | Gottingen 392 airfoil Max thickness 10.2% at 30% chord Max camber 4.8% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe392-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe392-il | 50,000 | 9 | 37.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe392-il | 50,000 | 5 | 38.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe392-il | 100,000 | 9 | 59.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe392-il | 100,000 | 5 | 58.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe392-il | 200,000 | 9 | 78.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe392-il | 200,000 | 5 | 77.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe392-il | 500,000 | 9 | 105.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe392-il | 500,000 | 5 | 102.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe392-il | 1,000,000 | 9 | 125.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe392-il | 1,000,000 | 5 | 120.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||