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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(as5045-il) AS5045 (15%) | AS5045 airfoil Ashok Gopalarathnam/Selig 15% airfoil Max thickness 15% at 37.5% chord Max camber 1% at 27.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (as5045-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| as5045-il | 50,000 | 9 | 30 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 50,000 | 5 | 29.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5045-il | 100,000 | 9 | 44 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 100,000 | 5 | 43.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5045-il | 200,000 | 9 | 59.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 200,000 | 5 | 56.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5045-il | 500,000 | 9 | 79.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 500,000 | 5 | 70.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5045-il | 1,000,000 | 9 | 92.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 1,000,000 | 5 | 81.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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