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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(sd7084-il) SD7084 (9.6%) | Selig/Donovan SD7084 low Reynolds number airfoil Max thickness 9.6% at 29.5% chord Max camber 2.3% at 38.9% chord | Remove Airfoil details Airfoil plotter |
(rg149-il) RG 14 9% AIRFOIL | Rolf Girsberger RG 14 (9%) airfoil Max thickness 9% at 31% chord Max camber 1.6% at 36% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sd7084-il,rg149-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sd7084-il | 50,000 | 9 | 31.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 50,000 | 5 | 35.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7084-il | 100,000 | 9 | 49.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 100,000 | 5 | 49.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7084-il | 200,000 | 9 | 65.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 200,000 | 5 | 63.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7084-il | 500,000 | 9 | 87.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 500,000 | 5 | 83.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7084-il | 1,000,000 | 9 | 104.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 1,000,000 | 5 | 98.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 50,000 | 9 | 33.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 50,000 | 5 | 34.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 100,000 | 9 | 48.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 100,000 | 5 | 46.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 200,000 | 9 | 63.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 200,000 | 5 | 57.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 500,000 | 9 | 81.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 500,000 | 5 | 70.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 1,000,000 | 9 | 90 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 1,000,000 | 5 | 84.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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