Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(mh18-il) MH 18 11.16% | Martin Hepperle MH 18 for F3D Pylon Racing Max thickness 11.1% at 36.8% chord Max camber 2.7% at 42.1% chord | Remove Airfoil details Airfoil plotter |
(fx79l120-il) FX 79-L-120 | Wortmann FX 79-L-120 symmetrical airfoil Max thickness 12.1% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(ag38-il) AG38 | Drela AG38 airfoil Max thickness 7% at 27.7% chord Max camber 2% at 36.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh18-il,fx79l120-il,ag38-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh18-il | 50,000 | 9 | 32.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 50,000 | 5 | 31.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh18-il | 100,000 | 9 | 53.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 100,000 | 5 | 53.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh18-il | 200,000 | 9 | 77.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 200,000 | 5 | 74.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh18-il | 500,000 | 9 | 108.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 500,000 | 5 | 96.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh18-il | 1,000,000 | 9 | 127.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 1,000,000 | 5 | 107.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l120-il | 50,000 | 9 | 27.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l120-il | 50,000 | 5 | 27.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l120-il | 100,000 | 9 | 40.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l120-il | 100,000 | 5 | 38 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l120-il | 200,000 | 9 | 52.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l120-il | 200,000 | 5 | 43.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l120-il | 500,000 | 9 | 58.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l120-il | 500,000 | 5 | 60.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l120-il | 1,000,000 | 9 | 73.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l120-il | 1,000,000 | 5 | 74.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag38-il | 50,000 | 9 | 34.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 50,000 | 5 | 36 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag38-il | 100,000 | 9 | 49.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 100,000 | 5 | 48.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag38-il | 200,000 | 9 | 64 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 200,000 | 5 | 59.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag38-il | 500,000 | 9 | 81.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 500,000 | 5 | 73.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag38-il | 1,000,000 | 9 | 92 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 1,000,000 | 5 | 85.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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