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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(sm701-il) SM701 | Somers / Maughmer SM701 airfoil Max thickness 16% at 36.3% chord Max camber 3% at 60.3% chord | Remove Airfoil details Airfoil plotter |
(fx6617a2-il) FX 66-17AII-182 AIRFOIL | Wortmann FX 66-17AII-182 airfoil Max thickness 18.2% at 33.9% chord Max camber 3.8% at 37.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sm701-il,fx6617a2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sm701-il | 50,000 | 9 | 27 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 50,000 | 5 | 30.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 100,000 | 9 | 50.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 100,000 | 5 | 46.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 200,000 | 9 | 68.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 200,000 | 5 | 64.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 500,000 | 9 | 95.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 500,000 | 5 | 79.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 1,000,000 | 9 | 110.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 1,000,000 | 5 | 93.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 50,000 | 9 | 4.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 50,000 | 5 | 8.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 100,000 | 9 | 5.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 100,000 | 5 | 29.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 200,000 | 9 | 65 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 200,000 | 5 | 67.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 500,000 | 9 | 104.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 500,000 | 5 | 102 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 1,000,000 | 9 | 131.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 1,000,000 | 5 | 125.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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