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 | ||
(goe432-il) GOE 432 AIRFOIL | Gottingen 432 airfoil Max thickness 7.7% at 20% chord Max camber 4.3% at 40% chord | Remove Airfoil details Airfoil plotter |
(fx73cl3152-il) FX 73-CL3-152 | Wortmann FX 73-CL3-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 8% at 43.5% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe432-il,fx73cl3152-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe432-il | 50,000 | 9 | 35.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe432-il | 50,000 | 5 | 40.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe432-il | 100,000 | 9 | 53.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe432-il | 100,000 | 5 | 56.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe432-il | 200,000 | 9 | 72.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe432-il | 200,000 | 5 | 72 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe432-il | 500,000 | 9 | 94.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe432-il | 500,000 | 5 | 88.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe432-il | 1,000,000 | 9 | 108 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe432-il | 1,000,000 | 5 | 107.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl3152-il | 50,000 | 9 | 5.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 50,000 | 5 | 28.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl3152-il | 100,000 | 9 | 38.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 100,000 | 5 | 50.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl3152-il | 200,000 | 9 | 64 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 200,000 | 5 | 71 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl3152-il | 500,000 | 9 | 99.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 500,000 | 5 | 100.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl3152-il | 1,000,000 | 9 | 129.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 1,000,000 | 5 | 128.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||