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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(sc1012r8-il) SIKORSKY SC1012R8 AIRFOIL | Sikorsky SC1012 R8 rotorcraft airfoil Max thickness 12% at 27.8% chord Max camber 2.7% at 21.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sc1012r8-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc1012r8-il | 50,000 | 9 | 23.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 50,000 | 5 | 26.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 100,000 | 9 | 34 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 100,000 | 5 | 37.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 200,000 | 9 | 46.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 200,000 | 5 | 50.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 500,000 | 9 | 68.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 500,000 | 5 | 72.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 1,000,000 | 9 | 88.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 1,000,000 | 5 | 90.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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