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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(naca663218-il) NACA 66(3)-218 | NACA 66(3)-218 airfoil Max thickness 18% at 45% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca642215-il) NACA 64(2)-215 | NACA 64(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(ah7476-il) AH-7-47-6 AIRFOIL | Althaus AH 7-476 airfoil Max thickness 5.9% at 20% chord Max camber 6.2% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca663218-il,naca642215-il,ah7476-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca663218-il | 50,000 | 9 | 19.3 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663218-il | 50,000 | 5 | 16.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca663218-il | 100,000 | 9 | 26.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663218-il | 100,000 | 5 | 22.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca663218-il | 200,000 | 9 | 38.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663218-il | 200,000 | 5 | 41.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca663218-il | 500,000 | 9 | 76.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663218-il | 500,000 | 5 | 72.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca663218-il | 1,000,000 | 9 | 99.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663218-il | 1,000,000 | 5 | 87.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca642215-il | 50,000 | 9 | 28.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642215-il | 50,000 | 5 | 26.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca642215-il | 100,000 | 9 | 47.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642215-il | 100,000 | 5 | 44.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca642215-il | 200,000 | 9 | 63.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642215-il | 200,000 | 5 | 58.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca642215-il | 500,000 | 9 | 85.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642215-il | 500,000 | 5 | 73.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca642215-il | 1,000,000 | 9 | 99.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642215-il | 1,000,000 | 5 | 79.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah7476-il | 50,000 | 9 | 48.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah7476-il | 50,000 | 5 | 48.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah7476-il | 100,000 | 9 | 75.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah7476-il | 100,000 | 5 | 74.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah7476-il | 200,000 | 9 | 107.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah7476-il | 200,000 | 5 | 103.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah7476-il | 500,000 | 9 | 148.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah7476-il | 500,000 | 5 | 110.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah7476-il | 1,000,000 | 9 | 138.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah7476-il | 1,000,000 | 5 | 112.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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