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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(naca651412-il) NACA 65(1)-412 | NACA 65(1)-412 airfoil Max thickness 12% at 39.9% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca4412-il) NACA 4412 | NACA 4412 airfoil Max thickness 12% at 30% chord Max camber 4% at 40% chord | Remove Airfoil details Airfoil plotter |
(naca0006-il) NACA 0006 | NACA 0006 airfoil Max thickness 6% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca0018-il) NACA 0018 | NACA 0018 airfoil Max thickness 18% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca63a210-il) NACA 63A210 | NACA 63A210 airfoil Max thickness 10% at 34.9% chord Max camber 1.3% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca2412-il) NACA 2412 | NACA 2412 airfoil Max thickness 12% at 30% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
(naca63206-il) NACA 63-206 | NACA 63-206 airfoil Max thickness 6% at 35% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (naca651412-il,naca4412-il,naca0006-il,naca0018-il,naca63a210-il,naca2412-il,naca63206-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca651412-il | 50,000 | 9 | 28.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 50,000 | 5 | 30.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 100,000 | 9 | 53 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 100,000 | 5 | 51.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 200,000 | 9 | 74.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 200,000 | 5 | 67.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 500,000 | 9 | 98.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 500,000 | 5 | 88.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 1,000,000 | 9 | 116.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 1,000,000 | 5 | 100.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 50,000 | 9 | 33.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 50,000 | 5 | 36.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 100,000 | 9 | 56.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 100,000 | 5 | 57.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 200,000 | 9 | 78.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 200,000 | 5 | 76.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 500,000 | 9 | 107.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 500,000 | 5 | 101.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 1,000,000 | 9 | 129.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 1,000,000 | 5 | 119.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0006-il | 50,000 | 9 | 24.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0006-il | 50,000 | 5 | 22.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0006-il | 100,000 | 9 | 32.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0006-il | 100,000 | 5 | 27.3 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0006-il | 200,000 | 9 | 38.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0006-il | 200,000 | 5 | 34 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0006-il | 500,000 | 5 | 47.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0006-il | 1,000,000 | 9 | 56.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0006-il | 1,000,000 | 5 | 60.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 50,000 | 9 | 22.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 50,000 | 5 | 26.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 100,000 | 9 | 37.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 100,000 | 5 | 38.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 200,000 | 9 | 50.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 200,000 | 5 | 48 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 500,000 | 9 | 65.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 500,000 | 5 | 61.5 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 1,000,000 | 9 | 77.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 1,000,000 | 5 | 73.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63a210-il | 50,000 | 9 | 28.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 50,000 | 5 | 31.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63a210-il | 100,000 | 9 | 37.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 100,000 | 5 | 40.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63a210-il | 200,000 | 9 | 44.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 200,000 | 5 | 48.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63a210-il | 500,000 | 9 | 52 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 500,000 | 5 | 58.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63a210-il | 1,000,000 | 9 | 58.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 1,000,000 | 5 | 70.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2412-il | 50,000 | 9 | 32.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2412-il | 50,000 | 5 | 34.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2412-il | 100,000 | 9 | 50 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2412-il | 100,000 | 5 | 49.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2412-il | 200,000 | 9 | 66.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2412-il | 200,000 | 5 | 62.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2412-il | 500,000 | 9 | 87.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2412-il | 500,000 | 5 | 78.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2412-il | 1,000,000 | 9 | 101.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2412-il | 1,000,000 | 5 | 87 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 50,000 | 9 | 24.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 50,000 | 5 | 31.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 100,000 | 9 | 43.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 100,000 | 5 | 41.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 200,000 | 9 | 57 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 200,000 | 5 | 52.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 500,000 | 9 | 72.4 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 500,000 | 5 | 58.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 1,000,000 | 9 | 80.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 1,000,000 | 5 | 69 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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