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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(s9032-il) S9032 (9%) | Selig S9032 (9%) symmetrical horizontal stab airfoil used on the Blackhawk R/C sailplane Max thickness 9% at 25% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s9032-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s9032-il | 50,000 | 9 | 23.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9032-il | 50,000 | 5 | 25 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9032-il | 100,000 | 9 | 32.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9032-il | 100,000 | 5 | 34.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9032-il | 200,000 | 9 | 43.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9032-il | 200,000 | 5 | 44.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9032-il | 500,000 | 9 | 60.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9032-il | 500,000 | 5 | 61 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9032-il | 1,000,000 | 9 | 74.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9032-il | 1,000,000 | 5 | 74.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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