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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(stcyr171-il) St. CYR 171 (Royer) | St. CYR 171 (Royer) airfoil Max thickness 11.1% at 30% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(sp4721la-po) SP4721LA | Saab-Pimenta High Performance low TE dB(A) noise 100 m Diameter Wind Turbine Main Airfoil in Quiet Mode of Operation Max thickness 21.4% at 34.8% chord Max camber 4.4% at 67.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (stcyr171-il,sp4721la-po)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| stcyr171-il | 50,000 | 9 | 24.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr171-il | 50,000 | 5 | 23.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr171-il | 100,000 | 9 | 33.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr171-il | 100,000 | 5 | 30 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr171-il | 200,000 | 9 | 47.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr171-il | 200,000 | 5 | 36.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr171-il | 500,000 | 9 | 43 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr171-il | 500,000 | 5 | 42.8 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr171-il | 1,000,000 | 9 | 45.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr171-il | 1,000,000 | 5 | 54.3 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sp4721la-po | 200,000 | 9 | 63.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sp4721la-po | 500,000 | 9 | 89 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sp4721la-po | 1,000,000 | 9 | 110.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sp4721la-po | 2,000,000 | 9 | 133.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sp4721la-po | 5,000,000 | 9 | 157.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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