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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(as5048-il) AS5048 (18%) | AS5048 airfoil Ashok Gopalarathnam/Selig 18% airfoil Max thickness 18% at 38.3% chord Max camber 0.8% at 77.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (as5048-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| as5048-il | 50,000 | 9 | 25 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 50,000 | 5 | 23.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5048-il | 100,000 | 9 | 41.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 100,000 | 5 | 40.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5048-il | 200,000 | 9 | 59.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 200,000 | 5 | 56.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5048-il | 500,000 | 9 | 81.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 500,000 | 5 | 71 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5048-il | 1,000,000 | 9 | 96.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 1,000,000 | 5 | 79.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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