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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(naca644221-il) NACA 64(4)-221 | NACA 64(4)-221 airfoil Max thickness 21% at 34.9% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca633218-il) NACA 63(3)-218 | NACA 63(3)-218 airfoil Max thickness 18% at 34.9% chord Max camber 1.1% at 24.9% chord | Remove Airfoil details Airfoil plotter |
(naca16009-il) NACA 16009 | NACA 16009 airfoil Max thickness 9% at 50% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca644221-il,naca633218-il,naca16009-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca644221-il | 50,000 | 9 | 9.4 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644221-il | 50,000 | 5 | 12.2 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644221-il | 100,000 | 9 | 24.1 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644221-il | 100,000 | 5 | 28.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644221-il | 200,000 | 9 | 57.2 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644221-il | 200,000 | 5 | 58.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644221-il | 500,000 | 9 | 90.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644221-il | 500,000 | 5 | 82.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644221-il | 1,000,000 | 9 | 111.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644221-il | 1,000,000 | 5 | 95.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633218-il | 50,000 | 9 | 22.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633218-il | 50,000 | 5 | 21.8 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633218-il | 100,000 | 9 | 43 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633218-il | 100,000 | 5 | 38.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633218-il | 200,000 | 9 | 51.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633218-il | 200,000 | 5 | 49.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633218-il | 500,000 | 9 | 67.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633218-il | 500,000 | 5 | 63.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633218-il | 1,000,000 | 9 | 81.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633218-il | 1,000,000 | 5 | 75.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16009-il | 50,000 | 9 | 18 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 50,000 | 5 | 19.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16009-il | 100,000 | 9 | 25.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 100,000 | 5 | 28.8 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16009-il | 200,000 | 9 | 39.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 200,000 | 5 | 34.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16009-il | 500,000 | 9 | 44.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 500,000 | 5 | 38 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16009-il | 1,000,000 | 9 | 47 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 1,000,000 | 5 | 47.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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