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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(rg14-il) RG 14 AIRFOIL | Rolf Girsberger RG 14 airfoil Max thickness 8.5% at 29.7% chord Max camber 1.6% at 39.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rg14-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg14-il | 50,000 | 9 | 33.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14-il | 50,000 | 5 | 34.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14-il | 100,000 | 9 | 49.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14-il | 100,000 | 5 | 47.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14-il | 200,000 | 9 | 64.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14-il | 200,000 | 5 | 59.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14-il | 500,000 | 9 | 83.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14-il | 500,000 | 5 | 74 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14-il | 1,000,000 | 9 | 95.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14-il | 1,000,000 | 5 | 84.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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