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 | ||
(naca651212a06-il) NACA 65(1)-212 a=0.6 | NACA 65(1)-212 a=0.6 airfoil Max thickness 12% at 40% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe331-il) GOE 331 (PFALZ 60) AIRFOIL | Gottingen 331 (Pfalz 60) airfoil Max thickness 10.6% at 29.9% chord Max camber 6.9% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(c141a-il) LOCKHEED C-141 BL0 AIRFOIL | Lockheed-Georgia C-141 transonic wing airfoils Max thickness 13% at 40.2% chord Max camber 1.1% at 64.5% chord | Remove Airfoil details Airfoil plotter |
(m11-il) NACA M11 AIRFOIL | NACA/Munk M-11 airfoil Max thickness 8.2% at 30% chord Max camber 1.9% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe05k-il) GOE 5K AIRFOIL | Gottingen 5K airfoil Max thickness 3.7% at 50% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(m16-il) NACA M16 AIRFOIL | NACA/Munk M-16 airfoil Max thickness 6.2% at 30% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (naca651212a06-il,goe331-il,c141a-il,m11-il,goe05k-il,m16-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca651212a06-il | 50,000 | 9 | 25.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212a06-il | 50,000 | 5 | 29.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212a06-il | 100,000 | 9 | 46.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212a06-il | 100,000 | 5 | 45.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212a06-il | 200,000 | 9 | 66.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212a06-il | 200,000 | 5 | 56.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212a06-il | 500,000 | 9 | 81.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212a06-il | 500,000 | 5 | 69.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212a06-il | 1,000,000 | 9 | 94.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212a06-il | 1,000,000 | 5 | 75.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 50,000 | 9 | 22.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 50,000 | 5 | 37.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 100,000 | 9 | 58.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 100,000 | 5 | 57.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 200,000 | 9 | 79.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 200,000 | 5 | 71.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 500,000 | 9 | 97.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 500,000 | 5 | 94.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 1,000,000 | 9 | 119.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 1,000,000 | 5 | 117.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141a-il | 50,000 | 9 | 29 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 50,000 | 5 | 27.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141a-il | 100,000 | 9 | 44.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 100,000 | 5 | 42 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141a-il | 200,000 | 9 | 62 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 200,000 | 5 | 47.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141a-il | 500,000 | 9 | 67.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 500,000 | 5 | 59.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141a-il | 1,000,000 | 9 | 76.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 1,000,000 | 5 | 72.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m11-il | 50,000 | 9 | 34.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 50,000 | 5 | 35.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m11-il | 100,000 | 9 | 50.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 100,000 | 5 | 48.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m11-il | 200,000 | 9 | 65.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 200,000 | 5 | 60.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m11-il | 500,000 | 9 | 84.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 500,000 | 5 | 75.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m11-il | 1,000,000 | 9 | 96.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 1,000,000 | 5 | 82.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe05k-il | 50,000 | 9 | 20.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe05k-il | 50,000 | 5 | 21.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe05k-il | 100,000 | 9 | 25.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe05k-il | 100,000 | 5 | 27.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe05k-il | 200,000 | 9 | 33.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe05k-il | 200,000 | 5 | 39.8 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe05k-il | 500,000 | 9 | 71.3 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe05k-il | 500,000 | 5 | 82.4 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe05k-il | 1,000,000 | 9 | 95.1 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe05k-il | 1,000,000 | 5 | 95.1 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 50,000 | 9 | 39 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 50,000 | 5 | 38.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 100,000 | 9 | 53.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 100,000 | 5 | 53.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 200,000 | 9 | 70.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 200,000 | 5 | 68.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 500,000 | 9 | 92.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 500,000 | 5 | 88.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 1,000,000 | 9 | 109.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 1,000,000 | 5 | 102.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||