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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(rg14a147-il) RG 14A-1.4/7.0 AIRFOIL | Rolf Girsberger RG 14A-1.4/7.0 airfoil Max thickness 7% at 29.7% chord Max camber 1.4% at 34.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rg14a147-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg14a147-il | 50,000 | 9 | 33.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14a147-il | 50,000 | 5 | 34.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14a147-il | 100,000 | 9 | 48.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14a147-il | 100,000 | 5 | 45.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14a147-il | 200,000 | 9 | 62.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14a147-il | 200,000 | 5 | 56.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14a147-il | 500,000 | 9 | 78.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14a147-il | 500,000 | 5 | 67.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14a147-il | 1,000,000 | 9 | 88 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14a147-il | 1,000,000 | 5 | 76.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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