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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(v43015-il) BOEING VERTOL V43015-2.48 AIRFOIL | Boeing-Vertol V43015-2.48 rotorcraft airfoil Max thickness 15% at 30% chord Max camber 3.7% at 15% chord | Remove Airfoil details Airfoil plotter |
(l1003-il) LIEBECK L1003 AIRFOIL | Liebeck high lift airfoil Max thickness 17.7% at 30% chord Max camber 6.5% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (v43015-il,l1003-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| v43015-il | 50,000 | 9 | 23.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 50,000 | 5 | 27.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 9 | 36.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 5 | 39.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 9 | 51.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 5 | 53.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 9 | 74.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 5 | 76.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 9 | 98.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 5 | 95 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 50,000 | 9 | 4.1 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 50,000 | 5 | 5.2 at α=17.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 100,000 | 9 | 4.5 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 100,000 | 5 | 7 at α=17.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 200,000 | 9 | 10.2 at α=18.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 200,000 | 5 | 10.1 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 500,000 | 9 | 74.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 500,000 | 5 | 68.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 1,000,000 | 9 | 104.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 1,000,000 | 5 | 68.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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