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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(ch10sm-il) CH10 (smoothed) | Chuch Hollinger CH 10-48-13 high lift low Reynolds number airfoil Max thickness 12.8% at 30.6% chord Max camber 10.2% at 49.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ch10sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ch10sm-il | 50,000 | 9 | 6.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 50,000 | 5 | 12.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 100,000 | 9 | 10.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 100,000 | 5 | 38.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 200,000 | 9 | 73.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 200,000 | 5 | 86.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 500,000 | 9 | 135.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 500,000 | 5 | 132.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 1,000,000 | 9 | 175.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 1,000,000 | 5 | 164 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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