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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(stcyr24-il) St. CYR 24 (Bartel 35-IIIC) | St. CYR 24 (Bartel 35-IIIC) airfoil Max thickness 12.4% at 30% chord Max camber 5.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (stcyr24-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| stcyr24-il | 50,000 | 9 | 29.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr24-il | 50,000 | 5 | 31.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr24-il | 100,000 | 9 | 56.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr24-il | 100,000 | 5 | 53.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr24-il | 200,000 | 9 | 82.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr24-il | 200,000 | 5 | 74.2 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr24-il | 500,000 | 9 | 116.5 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr24-il | 500,000 | 5 | 89.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr24-il | 1,000,000 | 9 | 126.9 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr24-il | 1,000,000 | 5 | 95.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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