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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(naca64209-il) NACA 64-209 | NACA 64-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(nacam6-il) NACA M6 | NACA M6 airfoil Max thickness 12% at 30% chord Max camber 2.1% at 30% chord | Remove Airfoil details Airfoil plotter |
(naca001065-il) NACA 0010-65 | NACA 0010-65 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(nacam3-il) NACA M3 | NACA M3 airfoil Max thickness 11.9% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(n9-il) N-9 | N-9 airfoil Max thickness 8.5% at 30% chord Max camber 2.7% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca64209-il,nacam6-il,naca001065-il,nacam3-il,n9-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca64209-il | 50,000 | 9 | 31.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64209-il | 50,000 | 5 | 32 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64209-il | 100,000 | 9 | 45.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64209-il | 100,000 | 5 | 43.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64209-il | 200,000 | 9 | 60.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64209-il | 200,000 | 5 | 53.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64209-il | 500,000 | 9 | 75.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64209-il | 500,000 | 5 | 60.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64209-il | 1,000,000 | 9 | 82.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64209-il | 1,000,000 | 5 | 70.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam6-il | 50,000 | 9 | 30.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 50,000 | 5 | 32.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam6-il | 100,000 | 9 | 49.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 100,000 | 5 | 49.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam6-il | 200,000 | 9 | 67.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 200,000 | 5 | 64.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam6-il | 500,000 | 9 | 89.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 500,000 | 5 | 72.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam6-il | 1,000,000 | 9 | 90.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 1,000,000 | 5 | 81 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001065-il | 50,000 | 9 | 20.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001065-il | 50,000 | 5 | 21.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001065-il | 100,000 | 9 | 27.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001065-il | 100,000 | 5 | 28.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001065-il | 200,000 | 9 | 40.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001065-il | 200,000 | 5 | 35.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001065-il | 500,000 | 9 | 43.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001065-il | 500,000 | 5 | 50.7 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001065-il | 1,000,000 | 9 | 57.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001065-il | 1,000,000 | 5 | 65.3 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 50,000 | 9 | 27.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 50,000 | 5 | 26.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 100,000 | 9 | 37.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 100,000 | 5 | 34.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 200,000 | 9 | 45.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 200,000 | 5 | 42.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 500,000 | 9 | 54.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 500,000 | 5 | 56.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 1,000,000 | 9 | 66.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 1,000,000 | 5 | 69.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n9-il | 50,000 | 9 | 36.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n9-il | 50,000 | 5 | 38.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n9-il | 100,000 | 9 | 53.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n9-il | 100,000 | 5 | 51.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n9-il | 200,000 | 9 | 68.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n9-il | 200,000 | 5 | 63.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n9-il | 500,000 | 9 | 84 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n9-il | 500,000 | 5 | 78.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n9-il | 1,000,000 | 9 | 96.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n9-il | 1,000,000 | 5 | 92.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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