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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(fx69pr281-il) FX 69-PR-281 | Wortmann FX 69-PR-281 airfoil Max thickness 28.1% at 22.2% chord Max camber 5.6% at 50% chord | Remove Airfoil details Airfoil plotter |
(mh38-il) MH 38 9.68% | Martin Hepperle MH 38 for Endurance Model Max thickness 9.7% at 31.6% chord Max camber 3.9% at 45.3% chord | Remove Airfoil details Airfoil plotter |
(goe395-il) GOE 395 AIRFOIL | Gottingen 395 airfoil Max thickness 6.1% at 19.9% chord Max camber 7% at 49.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx69pr281-il,mh38-il,goe395-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx69pr281-il | 50,000 | 9 | 3.4 at α=-5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69pr281-il | 50,000 | 5 | 6.4 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69pr281-il | 100,000 | 9 | 21.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69pr281-il | 100,000 | 5 | 26.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69pr281-il | 200,000 | 9 | 41.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69pr281-il | 200,000 | 5 | 35 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69pr281-il | 500,000 | 9 | 49.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69pr281-il | 500,000 | 5 | 47.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69pr281-il | 1,000,000 | 9 | 64.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69pr281-il | 1,000,000 | 5 | 61.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh38-il | 50,000 | 9 | 37.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh38-il | 50,000 | 5 | 37.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh38-il | 100,000 | 9 | 61.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh38-il | 100,000 | 5 | 61.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh38-il | 200,000 | 9 | 86.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh38-il | 200,000 | 5 | 85.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh38-il | 500,000 | 9 | 122.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh38-il | 500,000 | 5 | 114.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh38-il | 1,000,000 | 9 | 149.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh38-il | 1,000,000 | 5 | 133.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe395-il | 50,000 | 9 | 42.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe395-il | 50,000 | 5 | 43.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe395-il | 100,000 | 9 | 70.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe395-il | 100,000 | 5 | 71 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe395-il | 200,000 | 9 | 102.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe395-il | 200,000 | 5 | 100.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe395-il | 500,000 | 9 | 149.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe395-il | 500,000 | 5 | 117.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe395-il | 1,000,000 | 9 | 157.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe395-il | 1,000,000 | 5 | 124.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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