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 | ||
(goe703-il) GOE 703 AIRFOIL | Gottingen 703 airfoil Max thickness 19.4% at 30% chord Max camber 2.3% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe703-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe703-il | 50,000 | 9 | 5.5 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 50,000 | 5 | 22.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe703-il | 100,000 | 9 | 40 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 100,000 | 5 | 43 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe703-il | 200,000 | 9 | 63.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 200,000 | 5 | 49.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe703-il | 500,000 | 9 | 67 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 500,000 | 5 | 57.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe703-il | 1,000,000 | 9 | 75.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 1,000,000 | 5 | 65.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||