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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(r140sm-il) R140 12.04% (smoothed) | R140 Quickee 500 airfoil (smoothed) Max thickness 12% at 39.3% chord Max camber 0.4% at 39.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (r140sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| r140sm-il | 50,000 | 9 | 22.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 50,000 | 5 | 29.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140sm-il | 100,000 | 9 | 43 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 100,000 | 5 | 41.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140sm-il | 200,000 | 9 | 53.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 200,000 | 5 | 46.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140sm-il | 500,000 | 9 | 62 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 500,000 | 5 | 53.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140sm-il | 1,000,000 | 9 | 71.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 1,000,000 | 5 | 59.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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