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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(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 |
(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 |
(naca0008-il) NACA 0008 | NACA 0008 airfoil Max thickness 8% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca643618-il) NACA 64(3)-618 | NACA 64(3)-618 airfoil Max thickness 17.9% at 34.7% chord Max camber 3.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca633218-il,naca16015-il,naca0008-il,naca643618-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| 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 | |
| naca0008-il | 50,000 | 9 | 26.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 50,000 | 5 | 24.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0008-il | 100,000 | 9 | 34.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 100,000 | 5 | 30.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0008-il | 200,000 | 9 | 41.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 200,000 | 5 | 38.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0008-il | 500,000 | 9 | 50.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 500,000 | 5 | 56.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0008-il | 1,000,000 | 9 | 68.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 1,000,000 | 5 | 69.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643618-il | 50,000 | 9 | 18.6 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 50,000 | 5 | 14.9 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643618-il | 100,000 | 9 | 31.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 100,000 | 5 | 41.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643618-il | 200,000 | 9 | 74.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 200,000 | 5 | 73.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643618-il | 500,000 | 9 | 109.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 500,000 | 5 | 103.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643618-il | 1,000,000 | 9 | 136.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 1,000,000 | 5 | 124.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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