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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(lrn1007-il) lrn1007 | LRN(1)-1007 low Reynolds number airfoil Max thickness 7.3% at 39.8% chord Max camber 5.9% at 44.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (lrn1007-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| lrn1007-il | 50,000 | 9 | 30.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 50,000 | 5 | 35.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 100,000 | 9 | 51.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 100,000 | 5 | 55.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 200,000 | 9 | 81.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 200,000 | 5 | 98.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 500,000 | 9 | 125.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 500,000 | 5 | 150.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 1,000,000 | 9 | 127.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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