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 | ||
(geminism-il) GEMINI (smoothed) | GEMINI R/C sailplane airfoil (smoothed) Max thickness 15.4% at 34.2% chord Max camber 2.2% at 37.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (geminism-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| geminism-il | 50,000 | 9 | 8.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 50,000 | 5 | 28.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| geminism-il | 100,000 | 9 | 47.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 100,000 | 5 | 48.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| geminism-il | 200,000 | 9 | 66.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 200,000 | 5 | 65.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| geminism-il | 500,000 | 9 | 92.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 500,000 | 5 | 86.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| geminism-il | 1,000,000 | 9 | 110.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 1,000,000 | 5 | 100.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||