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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(spicasm-il) SPICA 11.73% smoothed | Anderson SPICA R/C sailplane airfoil (smoothed) Max thickness 11.7% at 30% chord Max camber 4.7% at 35% chord | Remove Airfoil details Airfoil plotter |
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Polars for (spicasm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| spicasm-il | 50,000 | 9 | 10.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| spicasm-il | 50,000 | 5 | 30.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| spicasm-il | 100,000 | 9 | 50.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| spicasm-il | 100,000 | 5 | 55.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| spicasm-il | 200,000 | 9 | 77.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| spicasm-il | 200,000 | 5 | 77.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| spicasm-il | 500,000 | 9 | 112.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| spicasm-il | 500,000 | 5 | 104.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| spicasm-il | 1,000,000 | 9 | 136.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| spicasm-il | 1,000,000 | 5 | 123.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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