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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(naca633418-il) NACA 63 | NACA 63 Max thickness 18% at 33.9% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(s3010-il) S3010-103-84 | Selig S3010 low Reynolds number airfoil Max thickness 10.3% at 25% chord Max camber 2.3% at 43.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca633418-il,s3010-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
---|---|---|---|---|---|---|---|
naca633418-il | 50,000 | 9 | 20.3 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
naca633418-il | 50,000 | 5 | 16.6 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
naca633418-il | 100,000 | 9 | 45.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
naca633418-il | 100,000 | 5 | 44.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
naca633418-il | 200,000 | 9 | 69.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
naca633418-il | 200,000 | 5 | 67.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
naca633418-il | 500,000 | 9 | 99.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
naca633418-il | 500,000 | 5 | 91.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
naca633418-il | 1,000,000 | 9 | 120.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
naca633418-il | 1,000,000 | 5 | 106.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
s3010-il | 50,000 | 9 | 28.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s3010-il | 50,000 | 5 | 36.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
s3010-il | 100,000 | 9 | 50.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s3010-il | 100,000 | 5 | 52.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
s3010-il | 200,000 | 9 | 70 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s3010-il | 200,000 | 5 | 68.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
s3010-il | 500,000 | 9 | 95.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s3010-il | 500,000 | 5 | 89.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
s3010-il | 1,000,000 | 9 | 113.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s3010-il | 1,000,000 | 5 | 104.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
Reynolds number calculator |