Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(naca16015-il) NACA 16-015 | NACA 16-015 airfoil Max thickness 15% at 50% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe481a-il) GOE 481A AIRFOIL | Gottingen 481A airfoil Max thickness 15.3% at 29.4% chord Max camber 5.5% at 39.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca16015-il,goe481a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca16015-il | 50,000 | 9 | 22.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 50,000 | 5 | 21.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 100,000 | 9 | 29.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 100,000 | 5 | 28.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 200,000 | 9 | 40.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 200,000 | 5 | 32 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 500,000 | 9 | 44.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 500,000 | 5 | 39.7 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 1,000,000 | 9 | 50.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 1,000,000 | 5 | 50.5 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481a-il | 50,000 | 9 | 6.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481a-il | 50,000 | 5 | 27.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481a-il | 100,000 | 9 | 47.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481a-il | 100,000 | 5 | 46.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481a-il | 200,000 | 9 | 63.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481a-il | 200,000 | 5 | 59 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481a-il | 500,000 | 9 | 80.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481a-il | 500,000 | 5 | 74.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481a-il | 1,000,000 | 9 | 95.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481a-il | 1,000,000 | 5 | 81.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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