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 | ||
(sm701-il) SM701 | Somers / Maughmer SM701 airfoil Max thickness 16% at 36.3% chord Max camber 3% at 60.3% chord | Remove Airfoil details Airfoil plotter |
(e864-il) EPPLER 864 STRUT AIRFOIL | Eppler E864 strut airfoil Max thickness 38.8% at 32.7% chord Max camber 0.1% at 10.8% chord | Remove Airfoil details Airfoil plotter |
(goe229-il) GOE 229 (MVA H.39) AIRFOIL | Gottingen 229 (MVA H.39) airfoil Max thickness 19.3% at 29% chord Max camber 5.9% at 49.1% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (sm701-il,e864-il,goe229-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sm701-il | 50,000 | 9 | 27 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 50,000 | 5 | 30.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 100,000 | 9 | 50.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 100,000 | 5 | 46.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 200,000 | 9 | 68.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 200,000 | 5 | 64.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 500,000 | 9 | 95.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 500,000 | 5 | 79.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 1,000,000 | 9 | 110.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 1,000,000 | 5 | 93.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e864-il | 50,000 | 9 | 2.5 at α=-8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e864-il | 50,000 | 5 | 3.7 at α=-2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e864-il | 100,000 | 9 | 4.2 at α=-4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e864-il | 100,000 | 5 | 4.9 at α=-3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e864-il | 200,000 | 9 | 7.6 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e864-il | 200,000 | 5 | 15 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e864-il | 500,000 | 9 | 37.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e864-il | 500,000 | 5 | 33.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e864-il | 1,000,000 | 9 | 50.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e864-il | 1,000,000 | 5 | 46.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 50,000 | 9 | 10.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 50,000 | 5 | 21.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 100,000 | 9 | 45.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 100,000 | 5 | 38.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 200,000 | 9 | 53.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 200,000 | 5 | 40.9 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 500,000 | 9 | 54.8 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 500,000 | 5 | 47.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 1,000,000 | 9 | 59.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 1,000,000 | 5 | 59.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||