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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(n10-il) N-10 | N-10 airfoil Max thickness 11.2% at 30% chord Max camber 3.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(lnv109a-il) LNV109A | Douglas/Liebeck LNV109A high lift airfoil Max thickness 13% at 23.5% chord Max camber 6% at 31.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n10-il,lnv109a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n10-il | 50,000 | 9 | 28.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n10-il | 50,000 | 5 | 37.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n10-il | 100,000 | 9 | 52 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n10-il | 100,000 | 5 | 52.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n10-il | 200,000 | 9 | 68.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n10-il | 200,000 | 5 | 68.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n10-il | 500,000 | 9 | 95.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n10-il | 500,000 | 5 | 92 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n10-il | 1,000,000 | 9 | 115.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n10-il | 1,000,000 | 5 | 109.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lnv109a-il | 50,000 | 9 | 5.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lnv109a-il | 50,000 | 5 | 9.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lnv109a-il | 100,000 | 9 | 7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lnv109a-il | 100,000 | 5 | 23.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lnv109a-il | 200,000 | 9 | 25.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lnv109a-il | 200,000 | 5 | 58.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lnv109a-il | 500,000 | 9 | 111.2 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lnv109a-il | 500,000 | 5 | 113.7 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lnv109a-il | 1,000,000 | 9 | 151.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lnv109a-il | 1,000,000 | 5 | 149.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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