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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(ste87391-il) EPPLER STE 87(-3)-914 AIRFOIL | Eppler STE 87(-3)-914 airfoil Max thickness 14.6% at 34.1% chord Max camber 4.2% at 58.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ste87391-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ste87391-il | 50,000 | 9 | 32.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 50,000 | 5 | 30.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87391-il | 100,000 | 9 | 51.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 100,000 | 5 | 45.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87391-il | 200,000 | 9 | 69.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 200,000 | 5 | 61.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87391-il | 500,000 | 9 | 97.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 500,000 | 5 | 92.5 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87391-il | 1,000,000 | 9 | 146 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 1,000,000 | 5 | 106.6 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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