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 | ||
(e361-il) EPPLER 361 AIRFOIL | Eppler E361 rotorcraft airfoil Max thickness 12.1% at 37.1% chord Max camber 1.7% at 27.4% chord | Remove Airfoil details Airfoil plotter |
(goe448-il) GOE 448 AIRFOIL | Gottingen 448 airfoil Max thickness 12.9% at 29.8% chord Max camber 10.5% at 39.8% chord | Remove Airfoil details Airfoil plotter |
(goe325-il) GOE 325 (PFALZ 54) AIRFOIL | Gottingen 325 (Pfalz 54) airfoil Max thickness 8.2% at 20% chord Max camber 4.6% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e361-il,goe448-il,goe325-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e361-il | 50,000 | 9 | 30.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e361-il | 50,000 | 5 | 31.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e361-il | 100,000 | 9 | 47.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e361-il | 100,000 | 5 | 46.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e361-il | 200,000 | 9 | 64.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e361-il | 200,000 | 5 | 54.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e361-il | 500,000 | 9 | 73.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e361-il | 500,000 | 5 | 70.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e361-il | 1,000,000 | 9 | 87.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e361-il | 1,000,000 | 5 | 84.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe448-il | 50,000 | 9 | 5.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe448-il | 50,000 | 5 | 11.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe448-il | 100,000 | 9 | 11.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe448-il | 100,000 | 5 | 37 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe448-il | 200,000 | 9 | 162 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe448-il | 200,000 | 5 | 74.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe448-il | 500,000 | 9 | 119.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe448-il | 500,000 | 5 | 102.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe448-il | 1,000,000 | 9 | 137.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe448-il | 1,000,000 | 5 | 123.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe325-il | 50,000 | 9 | 35.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe325-il | 50,000 | 5 | 37.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe325-il | 100,000 | 9 | 53.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe325-il | 100,000 | 5 | 55.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe325-il | 200,000 | 9 | 72.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe325-il | 200,000 | 5 | 73.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe325-il | 500,000 | 9 | 100 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe325-il | 500,000 | 5 | 98.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe325-il | 1,000,000 | 9 | 121.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe325-il | 1,000,000 | 5 | 117.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||