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 | ||
(nlr7301-il) NLR-7301 AIRFOIL | NLR NLR-7301 transonic airfoil Max thickness 16.5% at 35% chord Max camber 1.7% at 75% chord | Remove Airfoil details Airfoil plotter |
(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 |
(e216-il) E216 (10.4%) | Eppler E216 low Reynolds number airfoil Max thickness 10.4% at 26.2% chord Max camber 4.7% at 59% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (nlr7301-il,n63215b-il,e216-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nlr7301-il | 50,000 | 9 | 21 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 50,000 | 5 | 18.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr7301-il | 100,000 | 9 | 21.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 100,000 | 5 | 26.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr7301-il | 200,000 | 9 | 31 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 200,000 | 5 | 37.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr7301-il | 500,000 | 9 | 49.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 500,000 | 5 | 55.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr7301-il | 1,000,000 | 9 | 67.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 1,000,000 | 5 | 70.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| e216-il | 50,000 | 9 | 40.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e216-il | 50,000 | 5 | 43 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e216-il | 100,000 | 9 | 68.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e216-il | 100,000 | 5 | 68.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e216-il | 200,000 | 9 | 99.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e216-il | 200,000 | 5 | 94 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e216-il | 500,000 | 9 | 136.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e216-il | 500,000 | 5 | 115.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e216-il | 1,000,000 | 9 | 155.1 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e216-il | 1,000,000 | 5 | 127.4 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||