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 | ||
(mh27-il) MH 27 11.99% | Martin Hepperle MH 27 for F3D Pylon Racing (extended laminar flow) Max thickness 12% at 42.4% chord Max camber 1.4% at 42.4% chord | Remove Airfoil details Airfoil plotter |
(e334-il) EPPLER 334 AIRFOIL | Eppler E334 flying wing airfoil Max thickness 11.9% at 30.3% chord Max camber 4% at 25.4% chord | Remove Airfoil details Airfoil plotter |
(fx66a175-il) WORTMANN FX 66-17A-175 AIRFOIL | Wortmann FX 66-17A-175 airfoil Max thickness 17.5% at 33.9% chord Max camber 4.2% at 40.2% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (mh27-il,e334-il,fx66a175-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh27-il | 50,000 | 9 | 33.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh27-il | 50,000 | 5 | 30.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh27-il | 100,000 | 9 | 49.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh27-il | 100,000 | 5 | 46.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh27-il | 200,000 | 9 | 69.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh27-il | 200,000 | 5 | 54.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh27-il | 500,000 | 9 | 73.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh27-il | 500,000 | 5 | 54.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh27-il | 1,000,000 | 9 | 73.1 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh27-il | 1,000,000 | 5 | 61.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e334-il | 50,000 | 9 | 16.6 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e334-il | 50,000 | 5 | 27.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e334-il | 100,000 | 9 | 39.9 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e334-il | 100,000 | 5 | 48.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e334-il | 200,000 | 9 | 66.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e334-il | 200,000 | 5 | 70 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e334-il | 500,000 | 9 | 100.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e334-il | 500,000 | 5 | 98.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e334-il | 1,000,000 | 9 | 125.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e334-il | 1,000,000 | 5 | 116.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66a175-il | 50,000 | 9 | 4.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 50,000 | 5 | 12.3 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66a175-il | 100,000 | 9 | 12.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 100,000 | 5 | 34.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66a175-il | 200,000 | 9 | 70.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 200,000 | 5 | 71.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66a175-il | 500,000 | 9 | 103.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 500,000 | 5 | 100.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66a175-il | 1,000,000 | 9 | 128.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 1,000,000 | 5 | 124.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||