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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(naca664221-il) NACA 66(4)-221 | NACA 66(4)-221 airfoil Max thickness 21% at 45% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca663418-il) NACA 66(3)-418 | NACA 66(3)-418 airfoil Max thickness 18% at 44.9% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(ys915-il) YS-915 | YS915 hydrofoil (Shen / Eppler) Max thickness 9.1% at 36.1% chord Max camber 1.8% at 65.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca664221-il,naca663418-il,ys915-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca664221-il | 50,000 | 9 | 16.5 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 50,000 | 5 | 12.2 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca664221-il | 100,000 | 9 | 19.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 100,000 | 5 | 18.1 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca664221-il | 200,000 | 9 | 29.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 200,000 | 5 | 30.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca664221-il | 500,000 | 9 | 68.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 500,000 | 5 | 69.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca664221-il | 1,000,000 | 9 | 100.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 1,000,000 | 5 | 91.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca663418-il | 50,000 | 9 | 18.8 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663418-il | 50,000 | 5 | 16.8 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca663418-il | 100,000 | 9 | 27 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663418-il | 100,000 | 5 | 25.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca663418-il | 200,000 | 9 | 42.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663418-il | 200,000 | 5 | 44.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca663418-il | 500,000 | 9 | 91.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663418-il | 500,000 | 5 | 89.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca663418-il | 1,000,000 | 9 | 124 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663418-il | 1,000,000 | 5 | 114.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys915-il | 50,000 | 9 | 20.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys915-il | 50,000 | 5 | 21.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys915-il | 100,000 | 9 | 29.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys915-il | 100,000 | 5 | 34 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys915-il | 200,000 | 9 | 54 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys915-il | 200,000 | 5 | 51.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys915-il | 500,000 | 9 | 91.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys915-il | 500,000 | 5 | 73.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys915-il | 1,000,000 | 9 | 109.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys915-il | 1,000,000 | 5 | 79.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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