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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(l7769-il) LISSAMAN 7769 AIRFOIL | Lissaman 7769 human powered aircraft airfoil Max thickness 11% at 30% chord Max camber 4.4% at 30% chord | Remove Airfoil details Airfoil plotter |
(ls413-il) NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL | NASA/Langley LS(1)-0413 (GA(W)-2) general aviation airfoil Max thickness 12.9% at 37.5% chord Max camber 2.4% at 65% chord | Remove Airfoil details Airfoil plotter |
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Polars for (l7769-il,ls413-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| l7769-il | 50,000 | 9 | 6.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 50,000 | 5 | 15.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l7769-il | 100,000 | 9 | 32.3 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 100,000 | 5 | 39.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l7769-il | 200,000 | 9 | 72.6 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 200,000 | 5 | 74.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l7769-il | 500,000 | 9 | 113.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 500,000 | 5 | 111 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l7769-il | 1,000,000 | 9 | 143.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 1,000,000 | 5 | 136.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413-il | 50,000 | 9 | 35.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413-il | 50,000 | 5 | 33.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413-il | 100,000 | 9 | 53 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413-il | 100,000 | 5 | 48.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413-il | 200,000 | 9 | 69.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413-il | 200,000 | 5 | 65.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413-il | 500,000 | 9 | 96.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413-il | 500,000 | 5 | 82.5 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413-il | 1,000,000 | 9 | 112.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413-il | 1,000,000 | 5 | 86.4 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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