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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(s1223rtl-il) S1223 RTL | Richard T. LaSalle modification of the S1223 to S1223RTL Max thickness 13.5% at 19.9% chord Max camber 8.3% at 55.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s1223rtl-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s1223rtl-il | 50,000 | 9 | 31.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 50,000 | 5 | 35.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223rtl-il | 100,000 | 9 | 43.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 100,000 | 5 | 49.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223rtl-il | 200,000 | 9 | 98 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 200,000 | 5 | 64.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223rtl-il | 500,000 | 9 | 84 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 500,000 | 5 | 85.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223rtl-il | 1,000,000 | 9 | 106.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 1,000,000 | 5 | 106.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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