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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(lg10sc-il) LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL | Lockheed-Georgia/NASA/Blackwell rotorcraft airfoil Max thickness 10% at 32% chord Max camber 1.5% at 16% chord | Remove Airfoil details Airfoil plotter |
(fx60100sm-il) FX60-100 10.0% smoothed | Wortmann FX 60-100 airfoil (smoothed) Max thickness 10% at 27.9% chord Max camber 3.5% at 56.5% 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 (lg10sc-il,fx60100sm-il,lnv109a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| lg10sc-il | 50,000 | 9 | 25.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lg10sc-il | 50,000 | 5 | 27.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lg10sc-il | 100,000 | 9 | 35.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lg10sc-il | 100,000 | 5 | 39.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lg10sc-il | 200,000 | 9 | 48.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lg10sc-il | 200,000 | 5 | 53.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lg10sc-il | 500,000 | 9 | 73.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lg10sc-il | 500,000 | 5 | 74.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lg10sc-il | 1,000,000 | 9 | 92.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lg10sc-il | 1,000,000 | 5 | 90.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 50,000 | 9 | 40.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 50,000 | 5 | 42.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 100,000 | 9 | 62.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 100,000 | 5 | 61.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 200,000 | 9 | 85.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 200,000 | 5 | 79.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 500,000 | 9 | 112.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 500,000 | 5 | 91.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 1,000,000 | 9 | 120.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 1,000,000 | 5 | 100.7 at α=6.25° | 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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