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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(fx76mp160-il) FX 76-MP-160 | Wortmann FX 76-MP-160 airfoil Max thickness 16.1% at 33.9% chord Max camber 6.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe553-il) GOE 553 AIRFOIL | Gottingen 553 airfoil Max thickness 13.7% at 29.6% chord Max camber 4.7% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(goe381-il) GOE 381 AIRFOIL | Gottingen 381 airfoil Max thickness 6.4% at 30% chord Max camber 5.8% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe234-il) GOE 234 (MVA CA5) AIRFOIL | Gottingen 234 (MVA CA5) airfoil Max thickness 14.2% at 19.7% chord Max camber 9.2% at 49.7% chord | Remove Airfoil details Airfoil plotter |
(goe387-il) GOE 387 AIRFOIL | Gottingen 387 airfoil Max thickness 14.9% at 30% chord Max camber 5.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx76mp160-il,goe553-il,goe381-il,goe234-il,goe387-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx76mp160-il | 50,000 | 9 | 5.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp160-il | 50,000 | 5 | 16.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp160-il | 100,000 | 9 | 44.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp160-il | 100,000 | 5 | 40.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp160-il | 200,000 | 9 | 76.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp160-il | 200,000 | 5 | 72 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp160-il | 500,000 | 9 | 120.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp160-il | 500,000 | 5 | 109.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp160-il | 1,000,000 | 9 | 152.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp160-il | 1,000,000 | 5 | 110.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe553-il | 50,000 | 9 | 11.2 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 50,000 | 5 | 30.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe553-il | 100,000 | 9 | 45.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 100,000 | 5 | 54.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe553-il | 200,000 | 9 | 73 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 200,000 | 5 | 75 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe553-il | 500,000 | 9 | 105.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 500,000 | 5 | 102.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe553-il | 1,000,000 | 9 | 130.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 1,000,000 | 5 | 122.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe381-il | 50,000 | 9 | 37.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe381-il | 50,000 | 5 | 43 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe381-il | 100,000 | 9 | 58.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe381-il | 100,000 | 5 | 61.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe381-il | 200,000 | 9 | 80 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe381-il | 200,000 | 5 | 76.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe381-il | 500,000 | 9 | 100.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe381-il | 500,000 | 5 | 92 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe381-il | 1,000,000 | 9 | 111.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe381-il | 1,000,000 | 5 | 93.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe234-il | 50,000 | 9 | 10.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 50,000 | 5 | 27.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe234-il | 100,000 | 9 | 54.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 100,000 | 5 | 56.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe234-il | 200,000 | 9 | 77 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 200,000 | 5 | 79.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe234-il | 500,000 | 9 | 110.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 500,000 | 5 | 108.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe234-il | 1,000,000 | 9 | 137.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 1,000,000 | 5 | 127.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe387-il | 50,000 | 9 | 6.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe387-il | 50,000 | 5 | 22.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe387-il | 100,000 | 9 | 43.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe387-il | 100,000 | 5 | 50.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe387-il | 200,000 | 9 | 71.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe387-il | 200,000 | 5 | 69.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe387-il | 500,000 | 9 | 101 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe387-il | 500,000 | 5 | 93 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe387-il | 1,000,000 | 9 | 122.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe387-il | 1,000,000 | 5 | 114.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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