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 | ||
(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 |
(nlr1t-il) NLR-1T AIRFOIL | Bell/NASA/NLR NLR-1T rotorcraft airfoil Max thickness 8.7% at 38.3% chord Max camber 1.3% at 22.3% chord | Remove Airfoil details Airfoil plotter |
(naca2418-il) NACA 2418 | NACA 2418 airfoil Max thickness 18% at 30% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (naca24112-jf,nlr1t-il,naca2418-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| nlr1t-il | 50,000 | 9 | 29.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 50,000 | 5 | 28.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 100,000 | 9 | 38.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 100,000 | 5 | 39.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 200,000 | 9 | 53.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 200,000 | 5 | 52 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 500,000 | 9 | 70.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 500,000 | 5 | 68.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 1,000,000 | 9 | 84.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 1,000,000 | 5 | 80.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2418-il | 50,000 | 9 | 8.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 50,000 | 5 | 27.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2418-il | 100,000 | 9 | 42.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 100,000 | 5 | 44 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2418-il | 200,000 | 9 | 60.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 200,000 | 5 | 58.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2418-il | 500,000 | 9 | 83.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 500,000 | 5 | 75.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2418-il | 1,000,000 | 9 | 97.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 1,000,000 | 5 | 87.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||