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 | ||
(goe447-il) GOE 447 AIRFOIL | Gottingen 447 airfoil Max thickness 12.7% at 29.7% chord Max camber 8% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(arad13-il) ARA-D 13% AIRFOIL | Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 13% thick propeller airfoil Max thickness 13% at 25% chord Max camber 3.6% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe447-il,arad13-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe447-il | 50,000 | 9 | 6.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe447-il | 50,000 | 5 | 16 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe447-il | 100,000 | 9 | 40 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe447-il | 100,000 | 5 | 49.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe447-il | 200,000 | 9 | 84 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe447-il | 200,000 | 5 | 84.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe447-il | 500,000 | 9 | 129.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe447-il | 500,000 | 5 | 116.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe447-il | 1,000,000 | 9 | 161.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe447-il | 1,000,000 | 5 | 126.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 50,000 | 9 | 25.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 50,000 | 5 | 31.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 100,000 | 9 | 41.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 100,000 | 5 | 44.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 200,000 | 9 | 56.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 200,000 | 5 | 58.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 500,000 | 9 | 78.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 500,000 | 5 | 79.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 1,000,000 | 9 | 97.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 1,000,000 | 5 | 96.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||