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 | ||
(goe217-il) GOE 217 (MVA MK.12) AIRFOIL | Gottingen 217 (MVA MK.12) airfoil Max thickness 19% at 29.2% chord Max camber 6.3% at 59.4% chord | Remove Airfoil details Airfoil plotter |
(goe419-il) GOE 419 AIRFOIL | Gottingen 419 airfoil Max thickness 5.3% at 30% chord Max camber 4.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(mh24-il) MH 24 9.01% | Martin Hepperle MH 24 for F3D Pylon Racing (extended laminar flow) Max thickness 9% at 37.3% chord Max camber 1.2% at 37.3% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe217-il,goe419-il,mh24-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe217-il | 50,000 | 9 | 5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 50,000 | 5 | 21.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe217-il | 100,000 | 9 | 40.2 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 100,000 | 5 | 48.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe217-il | 200,000 | 9 | 67 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 200,000 | 5 | 70.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe217-il | 500,000 | 9 | 101.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 500,000 | 5 | 99.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe217-il | 1,000,000 | 9 | 127.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 1,000,000 | 5 | 119.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe419-il | 50,000 | 9 | 42.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe419-il | 50,000 | 5 | 40.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe419-il | 100,000 | 9 | 60 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe419-il | 100,000 | 5 | 59 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe419-il | 200,000 | 9 | 79.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe419-il | 200,000 | 5 | 78.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe419-il | 500,000 | 9 | 109.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe419-il | 500,000 | 5 | 102 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe419-il | 1,000,000 | 9 | 125 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe419-il | 1,000,000 | 5 | 119.3 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 50,000 | 9 | 34.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 50,000 | 5 | 33 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 100,000 | 9 | 50.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 100,000 | 5 | 47 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 200,000 | 9 | 68.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 200,000 | 5 | 59.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 500,000 | 9 | 79.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 500,000 | 5 | 61.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 1,000,000 | 9 | 74.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 1,000,000 | 5 | 70.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||