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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(esa40-il) ESA40 | Evans Simitar Airfoil ESA40 for R/C tailless aircraft Max thickness 10.7% at 27.1% chord Max camber 2% at 12% chord | Remove Airfoil details Airfoil plotter |
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Polars for (esa40-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| esa40-il | 50,000 | 9 | 16 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| esa40-il | 50,000 | 5 | 21.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| esa40-il | 100,000 | 9 | 25.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| esa40-il | 100,000 | 5 | 32.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| esa40-il | 200,000 | 9 | 39.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| esa40-il | 200,000 | 5 | 47.3 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| esa40-il | 500,000 | 9 | 66.3 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| esa40-il | 500,000 | 5 | 69.6 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| esa40-il | 1,000,000 | 9 | 87.5 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| esa40-il | 1,000,000 | 5 | 86.4 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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