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 | ||
(n63215b-il) NACA 63(2)-215 MOD B | NACA-NASA/AMES/Hicks 63(2)-215 MOD B airfoil Max thickness 15% at 30% chord Max camber 1.5% at 10% chord | Remove Airfoil details Airfoil plotter |
(n63015a-il) NACA 63-015A AIRFOIL | NACA 63-015A airfoil Max thickness 15% at 35% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(n63210-il) NACA 63-210 AIRFOIL | NACA 63-210 airfoil Max thickness 10% at 35% chord Max camber 1.1% at 60% chord | Remove Airfoil details Airfoil plotter |
(fx60100sm-il) FX60-100 10.0% smoothed | Wortmann FX 60-100 airfoil (smoothed) Max thickness 10% at 27.9% chord Max camber 3.5% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(n63010a-il) NACA 63A010 AIRFOIL | NACA 63-010A airfoil Max thickness 10% at 35% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (n63215b-il,n63015a-il,n63210-il,fx60100sm-il,n63010a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n63215b-il | 50,000 | 9 | 25.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 50,000 | 5 | 24.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 100,000 | 9 | 32.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 100,000 | 5 | 35.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 200,000 | 9 | 44.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 200,000 | 5 | 47.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 500,000 | 9 | 66.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 500,000 | 5 | 68.3 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 1,000,000 | 9 | 86.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 1,000,000 | 5 | 83.9 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63015a-il | 50,000 | 9 | 28.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63015a-il | 50,000 | 5 | 28.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63015a-il | 100,000 | 9 | 44.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63015a-il | 100,000 | 5 | 39.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63015a-il | 200,000 | 9 | 53.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63015a-il | 200,000 | 5 | 46.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63015a-il | 500,000 | 9 | 66.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63015a-il | 500,000 | 5 | 55.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63015a-il | 1,000,000 | 9 | 72.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63015a-il | 1,000,000 | 5 | 66.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 50,000 | 9 | 33.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 50,000 | 5 | 32 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 100,000 | 9 | 46.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 100,000 | 5 | 42.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 200,000 | 9 | 59.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 200,000 | 5 | 48.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 500,000 | 9 | 67.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 500,000 | 5 | 55.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 1,000,000 | 9 | 69 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 1,000,000 | 5 | 66.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 50,000 | 9 | 40.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 50,000 | 5 | 42.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 100,000 | 9 | 62.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 100,000 | 5 | 61.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 200,000 | 9 | 85.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 200,000 | 5 | 79.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 500,000 | 9 | 112.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 500,000 | 5 | 91.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 1,000,000 | 9 | 120.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 1,000,000 | 5 | 100.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63010a-il | 50,000 | 9 | 27.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63010a-il | 50,000 | 5 | 26.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63010a-il | 100,000 | 9 | 37.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63010a-il | 100,000 | 5 | 34.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63010a-il | 200,000 | 9 | 47.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63010a-il | 200,000 | 5 | 39.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63010a-il | 500,000 | 9 | 52.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63010a-il | 500,000 | 5 | 51 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63010a-il | 1,000,000 | 9 | 59.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63010a-il | 1,000,000 | 5 | 64.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||