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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(sc1095r8-il) SIKORSKY SC1094R8 AIRFOIL | Sikorsky/Velkoff SC1095 R8 rotorcraft airfoil Max thickness 9.3% at 26.5% chord Max camber 2.1% at 20.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sc1095r8-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc1095r8-il | 50,000 | 9 | 24.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1095r8-il | 50,000 | 5 | 27 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1095r8-il | 100,000 | 9 | 33.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1095r8-il | 100,000 | 5 | 37.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1095r8-il | 200,000 | 9 | 45.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1095r8-il | 200,000 | 5 | 50.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1095r8-il | 500,000 | 9 | 67.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1095r8-il | 500,000 | 5 | 72.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1095r8-il | 1,000,000 | 9 | 88 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1095r8-il | 1,000,000 | 5 | 91.7 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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