Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(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 |
(naca24112-jf) NACA 24112 | NACA 24112 5 digit reflex airfoil Max thickness 12% at 29.4% chord Max camber 1.7% at 20.6% chord | Remove Airfoil details Airfoil plotter |
(naca63209-il) NACA 63-209 | NACA 63-209 airfoil Max thickness 9% at 35% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca2410-il) NACA 2410 | NACA 2410 airfoil Max thickness 10% at 29.9% chord Max camber 2% at 40% 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 |
Drawing Options
Polars for (naca633218-il,naca24112-jf,naca63209-il,naca2410-il,naca4412-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 | |
| naca24112-jf | 50,000 | 9 | 19.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca24112-jf | 50,000 | 5 | 27.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca24112-jf | 100,000 | 9 | 37.3 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca24112-jf | 100,000 | 5 | 43.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca24112-jf | 200,000 | 9 | 57.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca24112-jf | 200,000 | 5 | 60.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca24112-jf | 500,000 | 9 | 84.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca24112-jf | 500,000 | 5 | 83 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca24112-jf | 1,000,000 | 9 | 105.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca24112-jf | 1,000,000 | 5 | 98.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 50,000 | 9 | 32.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 50,000 | 5 | 32.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 100,000 | 9 | 47.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 100,000 | 5 | 44.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 200,000 | 9 | 62 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 200,000 | 5 | 55.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 500,000 | 9 | 78 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 500,000 | 5 | 63.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 1,000,000 | 9 | 84.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 1,000,000 | 5 | 72.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 50,000 | 9 | 35.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 50,000 | 5 | 36.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 100,000 | 9 | 51.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 100,000 | 5 | 49.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 200,000 | 9 | 67.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 200,000 | 5 | 62 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 500,000 | 9 | 86.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 500,000 | 5 | 75.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 1,000,000 | 9 | 98.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 1,000,000 | 5 | 83.7 at α=3.25° | 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 | |
| Reynolds number calculator | |||||||