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 | ||
(goe281-il) GOE 281 (DAIMLER XII) AIRFOIL | Gottingen 281 (DAIMLER XII) airfoil Max thickness 8% at 30% chord Max camber 4.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe423-il) GOE 423 AIRFOIL | Gottingen 423 airfoil Max thickness 16.9% at 39.7% chord Max camber 5.1% at 39.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe281-il,goe423-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
---|---|---|---|---|---|---|---|
goe281-il | 50,000 | 9 | 36.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe281-il | 50,000 | 5 | 42.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe281-il | 100,000 | 9 | 59 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe281-il | 100,000 | 5 | 59.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe281-il | 200,000 | 9 | 79.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe281-il | 200,000 | 5 | 75.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe281-il | 500,000 | 9 | 101.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe281-il | 500,000 | 5 | 95.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe281-il | 1,000,000 | 9 | 118.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe281-il | 1,000,000 | 5 | 98.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe423-il | 50,000 | 9 | 4.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe423-il | 50,000 | 5 | 14.4 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe423-il | 100,000 | 9 | 22.8 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe423-il | 100,000 | 5 | 40.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe423-il | 200,000 | 9 | 69.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe423-il | 200,000 | 5 | 70.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe423-il | 500,000 | 9 | 105.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe423-il | 500,000 | 5 | 101.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe423-il | 1,000,000 | 9 | 133.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe423-il | 1,000,000 | 5 | 124.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
Reynolds number calculator |