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 | ||
(m12-il) NACA M12 AIRFOIL | NACA/Munk M-12 airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord | Remove Airfoil details Airfoil plotter |
(vr7b-il) BOEING-VERTOL VR-7 AIRFOIL WITH TAB | Boeing-Vertol VR-7 rotorcraft airfoil with tab Max thickness 12% at 33% chord Max camber 3% at 29% chord | Remove Airfoil details Airfoil plotter |
(m6-il) NACA M6 AIRFOIL | NACA/Munk M-6 airfoil Max thickness 12% at 30% chord Max camber 2.2% at 30% chord | Remove Airfoil details Airfoil plotter |
(e67-il) EPPLER 67 AIRFOIL | Eppler E67 low Reynolds number airfoil Max thickness 11.6% at 32.6% chord Max camber 3.7% at 51.6% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (m12-il,vr7b-il,m6-il,e67-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m12-il | 50,000 | 9 | 31.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 50,000 | 5 | 33.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 100,000 | 9 | 49 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 100,000 | 5 | 48.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 200,000 | 9 | 65.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 200,000 | 5 | 62.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 500,000 | 9 | 86.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 500,000 | 5 | 77.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 1,000,000 | 9 | 98.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 1,000,000 | 5 | 85.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 50,000 | 9 | 30.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 50,000 | 5 | 33.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 100,000 | 9 | 52.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 100,000 | 5 | 53.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 200,000 | 9 | 72.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 200,000 | 5 | 71.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 500,000 | 9 | 99.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 500,000 | 5 | 92.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 1,000,000 | 9 | 118.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 1,000,000 | 5 | 105.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m6-il | 50,000 | 9 | 30.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m6-il | 50,000 | 5 | 32 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m6-il | 100,000 | 9 | 48.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m6-il | 100,000 | 5 | 48.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m6-il | 200,000 | 9 | 66.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m6-il | 200,000 | 5 | 63.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m6-il | 500,000 | 9 | 87.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m6-il | 500,000 | 5 | 76.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m6-il | 1,000,000 | 9 | 97 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m6-il | 1,000,000 | 5 | 83.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 50,000 | 9 | 37.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 50,000 | 5 | 36.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 100,000 | 9 | 60.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 100,000 | 5 | 60.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 200,000 | 9 | 86.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 200,000 | 5 | 82.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 500,000 | 9 | 121.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 500,000 | 5 | 107.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 1,000,000 | 9 | 144.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 1,000,000 | 5 | 117.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||