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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(ag19-il) AG19 | Drela AG19 airfoil Max thickness 5.4% at 20.6% chord Max camber 2.2% at 44.2% chord | Remove Airfoil details Airfoil plotter |
(ag27-il) AG27 Bubble Dancer DLG by Mark Drela | Drela AG27 airfoil used on the Bubble Dancer R/C DLG Max thickness 6.1% at 21.7% chord Max camber 2.6% at 44% chord | Remove Airfoil details Airfoil plotter |
(ag13-il) AG13 | Drela AG13 airfoil Max thickness 5.8% at 21.3% chord Max camber 2% at 41.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag19-il,ag27-il,ag13-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag19-il | 50,000 | 9 | 36.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 50,000 | 5 | 37.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 100,000 | 9 | 51.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 100,000 | 5 | 48.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 200,000 | 9 | 66.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 200,000 | 5 | 60.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 500,000 | 9 | 81.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 500,000 | 5 | 77.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 1,000,000 | 9 | 95.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 1,000,000 | 5 | 90.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag27-il | 50,000 | 9 | 37.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag27-il | 50,000 | 5 | 39.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag27-il | 100,000 | 9 | 55.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag27-il | 100,000 | 5 | 53 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag27-il | 200,000 | 9 | 71.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag27-il | 200,000 | 5 | 65.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag27-il | 500,000 | 9 | 91.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag27-il | 500,000 | 5 | 81.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag27-il | 1,000,000 | 9 | 103.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag27-il | 1,000,000 | 5 | 95.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag13-il | 50,000 | 9 | 34.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag13-il | 50,000 | 5 | 35.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag13-il | 100,000 | 9 | 48.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag13-il | 100,000 | 5 | 47.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag13-il | 200,000 | 9 | 62.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag13-il | 200,000 | 5 | 59 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag13-il | 500,000 | 9 | 79.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag13-il | 500,000 | 5 | 75.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag13-il | 1,000,000 | 9 | 92.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag13-il | 1,000,000 | 5 | 88.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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