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 |
(la5055-il) LIEBECK LA5055 AIRFOIL | Liebeck high lift airfoil Max thickness 15.9% at 35% chord Max camber 5.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(lrn1015-il) NASA LRN 1015 (NASA TM 102840) | LRN 1015 airfoil used on the Northrop Grumman RQ-4 Global Hawk airfoil Max thickness 15.2% at 40% chord Max camber 4.9% at 44% 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,la5055-il,lrn1015-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 | |
| la5055-il | 50,000 | 9 | 4.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 50,000 | 5 | 8.7 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la5055-il | 100,000 | 9 | 18.7 at α=15.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 100,000 | 5 | 15.5 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la5055-il | 200,000 | 9 | 24.7 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 200,000 | 5 | 46.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la5055-il | 500,000 | 9 | 116.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 500,000 | 5 | 104.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la5055-il | 1,000,000 | 9 | 149.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 1,000,000 | 5 | 83.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1015-il | 50,000 | 9 | 21.9 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 50,000 | 5 | 20.2 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1015-il | 100,000 | 9 | 39.8 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 100,000 | 5 | 34 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1015-il | 200,000 | 9 | 70.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 200,000 | 5 | 72.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1015-il | 500,000 | 9 | 127.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 500,000 | 5 | 112.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1015-il | 1,000,000 | 9 | 154.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 1,000,000 | 5 | 134.4 at α=3.25° | 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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