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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(sa7025-il) SA7025 | Selig / Ashok Gopalarathnam SA7025 low Reynolds number airfoil Max thickness 8% at 29.2% chord Max camber 3.6% at 43.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sa7025-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sa7025-il | 50,000 | 9 | 38.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7025-il | 50,000 | 5 | 41.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7025-il | 100,000 | 9 | 60.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7025-il | 100,000 | 5 | 60.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7025-il | 200,000 | 9 | 83.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7025-il | 200,000 | 5 | 77.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7025-il | 500,000 | 9 | 111.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7025-il | 500,000 | 5 | 98.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7025-il | 1,000,000 | 9 | 129.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7025-il | 1,000,000 | 5 | 112.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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