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 | ||
(nasasc2-0714-il) SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) | NASA SC(2)-0714 airfoil (Ref. NASA TP-2890) Max thickness 13.9% at 37% chord Max camber 2.5% at 80% chord | Remove Airfoil details Airfoil plotter |
(lwk80150k25-il) LWK 80-150/K25 | LWK 80-150/K25 symmetrical airfoil Max thickness 15% at 40.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca747a415-il) NACA 747A415 | NACA 747A415 airfoil Max thickness 15% at 40.2% chord Max camber 3% at 35% chord | Remove Airfoil details Airfoil plotter |
(naca632a015-il) NACA 63(2)A-015 | NACA 63(2)A-015 airfoil Max thickness 15% at 37.1% chord Max camber 1.7% at 14.6% chord | Remove Airfoil details Airfoil plotter |
(fx78k140a20-il) FX 78-K-140 A/20 | Wortmann FX 78-K-140 airfoil for use with flaps (K) A/20 Max thickness 14.1% at 43.5% chord Max camber 4.4% at 43.5% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (nasasc2-0714-il,lwk80150k25-il,naca747a415-il,naca632a015-il,fx78k140a20-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nasasc2-0714-il | 50,000 | 9 | 24.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 50,000 | 5 | 22.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 100,000 | 9 | 28.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 100,000 | 5 | 31.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 200,000 | 9 | 36.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 200,000 | 5 | 43.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 500,000 | 9 | 66 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 500,000 | 5 | 64 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 1,000,000 | 9 | 83.7 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 1,000,000 | 5 | 80 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80150k25-il | 50,000 | 9 | 28 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80150k25-il | 50,000 | 5 | 23.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80150k25-il | 100,000 | 9 | 38.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80150k25-il | 100,000 | 5 | 26.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80150k25-il | 200,000 | 9 | 38.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80150k25-il | 200,000 | 5 | 35.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80150k25-il | 500,000 | 9 | 52.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80150k25-il | 500,000 | 5 | 44 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80150k25-il | 1,000,000 | 9 | 59.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80150k25-il | 1,000,000 | 5 | 55.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 50,000 | 9 | 19 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 50,000 | 5 | 17 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 100,000 | 9 | 37.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 100,000 | 5 | 44.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 200,000 | 9 | 73.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 200,000 | 5 | 66.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 500,000 | 9 | 97.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 500,000 | 5 | 92.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 1,000,000 | 9 | 120.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 1,000,000 | 5 | 110.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca632a015-il | 50,000 | 9 | 23.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632a015-il | 50,000 | 5 | 29.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca632a015-il | 100,000 | 9 | 45.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632a015-il | 100,000 | 5 | 45.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca632a015-il | 200,000 | 9 | 59.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632a015-il | 200,000 | 5 | 55.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca632a015-il | 500,000 | 9 | 76.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632a015-il | 500,000 | 5 | 72.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca632a015-il | 1,000,000 | 9 | 93.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632a015-il | 1,000,000 | 5 | 84.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140a20-il | 50,000 | 9 | 16.8 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140a20-il | 50,000 | 5 | 15.8 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140a20-il | 100,000 | 9 | 25.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140a20-il | 100,000 | 5 | 27.8 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140a20-il | 200,000 | 9 | 54.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140a20-il | 200,000 | 5 | 57.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140a20-il | 500,000 | 9 | 118.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140a20-il | 500,000 | 5 | 111.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140a20-il | 1,000,000 | 9 | 147.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140a20-il | 1,000,000 | 5 | 142.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||