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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(us1000root-il) US1000ROOT | Great Planes R/C Ultra-Sport 1000 airfoil Max thickness 18.6% at 27.1% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (us1000root-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| us1000root-il | 50,000 | 9 | 19 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 50,000 | 5 | 24.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 100,000 | 9 | 38.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 100,000 | 5 | 38.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 200,000 | 9 | 49.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 200,000 | 5 | 44.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 500,000 | 9 | 49.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 500,000 | 5 | 43.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 1,000,000 | 9 | 52.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 1,000,000 | 5 | 45.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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