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 | ||
(eh1090-il) EH 1.0/9.0 | John Yost EH 1.0/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 1% at 25.9% chord | Remove Airfoil details Airfoil plotter |
(goe316-il) GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL | Gottingen 316 (Hansa-Brandenburg IV.5) airfoil Max thickness 9.1% at 29.9% chord Max camber 4.2% at 29.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (eh1090-il,goe316-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| eh1090-il | 50,000 | 9 | 29.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1090-il | 50,000 | 5 | 31.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh1090-il | 100,000 | 9 | 43.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1090-il | 100,000 | 5 | 43 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh1090-il | 200,000 | 9 | 56.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1090-il | 200,000 | 5 | 54.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh1090-il | 500,000 | 9 | 74.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1090-il | 500,000 | 5 | 68.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh1090-il | 1,000,000 | 9 | 84.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1090-il | 1,000,000 | 5 | 73.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe316-il | 50,000 | 9 | 23.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe316-il | 50,000 | 5 | 34.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe316-il | 100,000 | 9 | 50.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe316-il | 100,000 | 5 | 52 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe316-il | 200,000 | 9 | 71.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe316-il | 200,000 | 5 | 72 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe316-il | 500,000 | 9 | 100.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe316-il | 500,000 | 5 | 98.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe316-il | 1,000,000 | 9 | 123.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe316-il | 1,000,000 | 5 | 118.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||