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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(aquilasm-il) AQUILA 9.3% smoothed | AQUILA R/C sailplane airfoil Max thickness 9.4% at 31.3% chord Max camber 4% at 34.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (aquilasm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| aquilasm-il | 50,000 | 9 | 25.3 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 50,000 | 5 | 37 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| aquilasm-il | 100,000 | 9 | 51.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 100,000 | 5 | 56.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| aquilasm-il | 200,000 | 9 | 74.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 200,000 | 5 | 75 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| aquilasm-il | 500,000 | 9 | 104.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 500,000 | 5 | 99.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| aquilasm-il | 1,000,000 | 9 | 127.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 1,000,000 | 5 | 118.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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