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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(s9027-il) S9027 (8%) | Selig S9027 (8%) symmetrical vertical stab airfoil used on the Opus R/C sailplane Max thickness 8% at 22.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s9027-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s9027-il | 50,000 | 9 | 22.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 50,000 | 5 | 23.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 100,000 | 9 | 30.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 100,000 | 5 | 32.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 200,000 | 9 | 40.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 200,000 | 5 | 43.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 500,000 | 9 | 57.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 500,000 | 5 | 59.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 1,000,000 | 9 | 71.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 1,000,000 | 5 | 73.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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