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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(lds2-il) LDS-2 AIRFOIL | LDS-2 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 45% chord | Remove Airfoil details Airfoil plotter |
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Polars for (lds2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| lds2-il | 50,000 | 9 | 34 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lds2-il | 50,000 | 5 | 33.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lds2-il | 100,000 | 9 | 52.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lds2-il | 100,000 | 5 | 50.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lds2-il | 200,000 | 9 | 72.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lds2-il | 200,000 | 5 | 66.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lds2-il | 500,000 | 9 | 97.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lds2-il | 500,000 | 5 | 77.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lds2-il | 1,000,000 | 9 | 106.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lds2-il | 1,000,000 | 5 | 85.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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