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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(goe324-il) GOE 324 (HANSA-BRANDENBURG) AIRFOIL | Gottingen 324 (Hansa-Brandenburg) airfoil Max thickness 13.1% at 29.8% chord Max camber 5.9% at 29.8% chord | Remove Airfoil details Airfoil plotter |
(goe504-il) GOE 504 AIRFOIL | Gottingen 504 airfoil Max thickness 18% at 29.2% chord Max camber 5.4% at 39.2% chord | Remove Airfoil details Airfoil plotter |
(fx74cl5140-il) FX74_CL5_140 | Wortmann FX 74-CL5-140 high lift airfoil Max thickness 14% at 30.9% chord Max camber 9.9% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(mh117-il) MH 117 9.8% | Martin Hepperle MH 117 for a propeller for ultralight (tip) Max thickness 9.8% at 29.1% chord Max camber 2.7% at 44.6% chord | Remove Airfoil details Airfoil plotter |
(fx66h80-il) FX 66-H-80 | Wortmann FX 66-H-80 airfoil Max thickness 8% at 27.9% chord Max camber 2.5% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe324-il,goe504-il,fx74cl5140-il,mh117-il,fx66h80-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe324-il | 50,000 | 9 | 8.3 at α=-3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 50,000 | 5 | 20 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe324-il | 100,000 | 9 | 33.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 100,000 | 5 | 49.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe324-il | 200,000 | 9 | 70.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 200,000 | 5 | 74.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe324-il | 500,000 | 9 | 108.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 500,000 | 5 | 104.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe324-il | 1,000,000 | 9 | 136.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 1,000,000 | 5 | 124 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe504-il | 50,000 | 9 | 3.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 50,000 | 5 | 13.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe504-il | 100,000 | 9 | 34.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 100,000 | 5 | 43.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe504-il | 200,000 | 9 | 66.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 200,000 | 5 | 62.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe504-il | 500,000 | 9 | 91.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 500,000 | 5 | 85.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe504-il | 1,000,000 | 9 | 114.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 1,000,000 | 5 | 104.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 50,000 | 9 | 6.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 50,000 | 5 | 18.3 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 100,000 | 9 | 33.1 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 100,000 | 5 | 46.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 200,000 | 9 | 72.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 200,000 | 5 | 73.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 500,000 | 9 | 118.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 500,000 | 5 | 115.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 1,000,000 | 9 | 156.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 1,000,000 | 5 | 149.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh117-il | 50,000 | 9 | 36.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 50,000 | 5 | 38.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh117-il | 100,000 | 9 | 56.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 100,000 | 5 | 55.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh117-il | 200,000 | 9 | 77 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 200,000 | 5 | 72 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh117-il | 500,000 | 9 | 102.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 500,000 | 5 | 90.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh117-il | 1,000,000 | 9 | 120.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 1,000,000 | 5 | 100.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 50,000 | 9 | 32.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 50,000 | 5 | 31.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 100,000 | 9 | 47.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 100,000 | 5 | 47.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 200,000 | 9 | 63 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 200,000 | 5 | 62.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 500,000 | 9 | 87.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 500,000 | 5 | 83.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 1,000,000 | 9 | 105.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 1,000,000 | 5 | 98.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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