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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(fx67k170-il) FX 67-K-170/17 AIRFOIL | Wortmann FX 67-K-170/17 airfoil Max thickness 17% at 40.2% chord Max camber 5.1% at 43.5% 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 |
(fx69274-il) WORTMANN FX 69-274 | Wortmann FX 69-274 airfoil Max thickness 27.4% at 33.9% chord Max camber 3.2% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(fx77080-il) WORTMANN FX 77-080 | Wortmann FX 77-080 symmetrical airfoil Max thickness 8% at 27.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(fxlv152-il) WORTMANN FX L V-152 AIRFOIL | Wortmann FX L V-152 airfoil Max thickness 15.3% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe229-il) GOE 229 (MVA H.39) AIRFOIL | Gottingen 229 (MVA H.39) airfoil Max thickness 19.3% at 29% chord Max camber 5.9% at 49.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx67k170-il,fx79l120-il,fx69274-il,fx77080-il,fxlv152-il,goe229-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx67k170-il | 50,000 | 9 | 5 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k170-il | 50,000 | 5 | 11.8 at α=14.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k170-il | 100,000 | 9 | 20.1 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k170-il | 100,000 | 5 | 19.9 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k170-il | 200,000 | 9 | 36.6 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k170-il | 200,000 | 5 | 48.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k170-il | 500,000 | 9 | 116.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k170-il | 500,000 | 5 | 111.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k170-il | 1,000,000 | 9 | 152.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k170-il | 1,000,000 | 5 | 141.3 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 | |
| fx69274-il | 50,000 | 9 | 1.6 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69274-il | 100,000 | 9 | 1.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69274-il | 200,000 | 9 | 36 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69274-il | 500,000 | 9 | 65.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69274-il | 1,000,000 | 9 | 81.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77080-il | 50,000 | 9 | 24.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77080-il | 50,000 | 5 | 23.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77080-il | 100,000 | 9 | 33.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77080-il | 100,000 | 5 | 33.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77080-il | 200,000 | 9 | 42 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77080-il | 200,000 | 5 | 43.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77080-il | 500,000 | 9 | 58.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77080-il | 500,000 | 5 | 58.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77080-il | 1,000,000 | 9 | 71.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77080-il | 1,000,000 | 5 | 72.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxlv152-il | 50,000 | 9 | 27.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxlv152-il | 50,000 | 5 | 27.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxlv152-il | 100,000 | 9 | 42.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxlv152-il | 100,000 | 5 | 38.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxlv152-il | 200,000 | 9 | 52.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxlv152-il | 200,000 | 5 | 45.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxlv152-il | 500,000 | 9 | 59.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxlv152-il | 500,000 | 5 | 53.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxlv152-il | 1,000,000 | 9 | 66.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxlv152-il | 1,000,000 | 5 | 62.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 50,000 | 9 | 10.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 50,000 | 5 | 21.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 100,000 | 9 | 45.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 100,000 | 5 | 38.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 200,000 | 9 | 53.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 200,000 | 5 | 40.9 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 500,000 | 9 | 54.8 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 500,000 | 5 | 47.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 1,000,000 | 9 | 59.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 1,000,000 | 5 | 59.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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