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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(stcyr172-il) St. CYR 172 (Royer) | St. CYR 172 (Royer) airfoil Max thickness 13.6% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (stcyr172-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| stcyr172-il | 50,000 | 9 | 22.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr172-il | 50,000 | 5 | 27 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr172-il | 100,000 | 9 | 37.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr172-il | 100,000 | 5 | 38.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr172-il | 200,000 | 9 | 51.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr172-il | 200,000 | 5 | 50.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr172-il | 500,000 | 9 | 66.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr172-il | 500,000 | 5 | 61.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr172-il | 1,000,000 | 9 | 74.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr172-il | 1,000,000 | 5 | 75.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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