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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(fx63158-il) FX 63-158 AIRFOIL | Wortmann FX 63-158 airfoil Max thickness 15.8% at 33.9% chord Max camber 3.8% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(mrc-20-il) MRC-20 | Drela MRC-20 Max thickness 15.6% at 38.2% chord Max camber 2.9% at 48% chord | Remove Airfoil details Airfoil plotter |
(goe550-il) GOE 550 AIRFOIL | Gottingen 550 airfoil Max thickness 13% at 20% chord Max camber 4.3% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe11k-il) GOE 11K AIRFOIL | Gottingen 11K airfoil Max thickness 7.5% at 50% chord Max camber 2.7% at 60% chord | Remove Airfoil details Airfoil plotter |
(sa7036-il) SA7036 | Selig / Ashok Gopalarathnam SA7036 Max thickness 9.2% at 28.1% chord Max camber 2.6% at 42.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx63158-il,mrc-20-il,goe550-il,goe11k-il,sa7036-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx63158-il | 50,000 | 9 | 6.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 50,000 | 5 | 18.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63158-il | 100,000 | 9 | 47.5 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 100,000 | 5 | 51.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63158-il | 200,000 | 9 | 72.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 200,000 | 5 | 67.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63158-il | 500,000 | 9 | 76.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 500,000 | 5 | 70.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63158-il | 1,000,000 | 9 | 85 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 1,000,000 | 5 | 81.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 50,000 | 9 | 23.9 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 50,000 | 5 | 29.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 100,000 | 9 | 50.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 100,000 | 5 | 50.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 200,000 | 9 | 73.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 200,000 | 5 | 68.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 500,000 | 9 | 99.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 500,000 | 5 | 86.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 1,000,000 | 9 | 114.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 1,000,000 | 5 | 100.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe550-il | 50,000 | 9 | 27.6 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 50,000 | 5 | 33.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe550-il | 100,000 | 9 | 53.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 100,000 | 5 | 56.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe550-il | 200,000 | 9 | 76.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 200,000 | 5 | 75.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe550-il | 500,000 | 9 | 106.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 500,000 | 5 | 98.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe550-il | 1,000,000 | 9 | 127.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 1,000,000 | 5 | 114.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe11k-il | 50,000 | 9 | 28.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 50,000 | 5 | 31.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe11k-il | 100,000 | 9 | 41.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 100,000 | 5 | 49 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe11k-il | 200,000 | 9 | 72.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 200,000 | 5 | 72.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe11k-il | 500,000 | 9 | 109.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 500,000 | 5 | 99.4 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe11k-il | 1,000,000 | 9 | 122.4 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 1,000,000 | 5 | 87.1 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7036-il | 50,000 | 9 | 33.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7036-il | 50,000 | 5 | 38.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7036-il | 100,000 | 9 | 53.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7036-il | 100,000 | 5 | 54.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7036-il | 200,000 | 9 | 73 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7036-il | 200,000 | 5 | 69.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7036-il | 500,000 | 9 | 97.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7036-il | 500,000 | 5 | 88.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7036-il | 1,000,000 | 9 | 114 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7036-il | 1,000,000 | 5 | 103.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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