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 | ||
(naca0018-il) NACA 0018 | NACA 0018 airfoil Max thickness 18% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca66-018-il) NACA 66-018 | NACA 66-018 airfoil Max thickness 18% at 45% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(ncambre-il) ONERA NACA CAMBRE AIRFOIL | ONERA/Aerospatiale NACA-CAMBRE rotorcraft airfoil Max thickness 11.5% at 31.2% chord Max camber 1.4% at 15.9% chord | Remove Airfoil details Airfoil plotter |
(naca2408-il) NACA 2408 | NACA 2408 airfoil Max thickness 8% at 29.9% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (naca0018-il,naca66-018-il,ncambre-il,naca2408-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| naca66-018-il | 50,000 | 9 | 20.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 50,000 | 5 | 15.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 100,000 | 9 | 31.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 100,000 | 5 | 18.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 200,000 | 9 | 31 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 200,000 | 5 | 34.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 500,000 | 9 | 57.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 500,000 | 5 | 50.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 1,000,000 | 9 | 72 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 1,000,000 | 5 | 57.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ncambre-il | 50,000 | 9 | 26.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 50,000 | 5 | 29.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ncambre-il | 100,000 | 9 | 39.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 100,000 | 5 | 41.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ncambre-il | 200,000 | 9 | 52.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 200,000 | 5 | 54.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ncambre-il | 500,000 | 9 | 73.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 500,000 | 5 | 73 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ncambre-il | 1,000,000 | 9 | 90.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 1,000,000 | 5 | 88 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 50,000 | 9 | 37.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 50,000 | 5 | 36.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 100,000 | 9 | 52.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 100,000 | 5 | 48.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 200,000 | 9 | 66.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 200,000 | 5 | 58.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 500,000 | 9 | 80.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 500,000 | 5 | 67.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 1,000,000 | 9 | 86.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 1,000,000 | 5 | 82.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||