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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(rg15a213-il) RG 15A 2.5/13.0 AIRFOIL | Rolf Girsberger RG 15A 2.5/13.0 airfoil Max thickness 13% at 30.2% chord Max camber 2.5% at 39.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rg15a213-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg15a213-il | 50,000 | 9 | 29.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a213-il | 50,000 | 5 | 34.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a213-il | 100,000 | 9 | 50.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a213-il | 100,000 | 5 | 51.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a213-il | 200,000 | 9 | 69.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a213-il | 200,000 | 5 | 66.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a213-il | 500,000 | 9 | 93.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a213-il | 500,000 | 5 | 84.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a213-il | 1,000,000 | 9 | 108.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a213-il | 1,000,000 | 5 | 96.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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