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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(rg1410-il) RG 14 10% AIRFOIL | Rolf Girsberger RG 14 (10%) airfoil Max thickness 10% at 31% chord Max camber 1.6% at 36% chord | Remove Airfoil details Airfoil plotter |
(e205-il) E205 (10.48%) | Eppler E205 low Reynolds number airfoil Max thickness 10.5% at 29.7% chord Max camber 2.5% at 38.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rg1410-il,e205-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg1410-il | 50,000 | 9 | 32.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1410-il | 50,000 | 5 | 33.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1410-il | 100,000 | 9 | 48.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1410-il | 100,000 | 5 | 46.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1410-il | 200,000 | 9 | 63.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1410-il | 200,000 | 5 | 58.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1410-il | 500,000 | 9 | 82.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1410-il | 500,000 | 5 | 71.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1410-il | 1,000,000 | 9 | 89.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1410-il | 1,000,000 | 5 | 85.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 50,000 | 9 | 32.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 50,000 | 5 | 34.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 100,000 | 9 | 53.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 100,000 | 5 | 54.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 200,000 | 9 | 75.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 200,000 | 5 | 74 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 500,000 | 9 | 105.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 500,000 | 5 | 98.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 1,000,000 | 9 | 128.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 1,000,000 | 5 | 116.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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