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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(a63a108c-il) NASA/AMES 63A108 MOD C AIRFOIL | NASA/AMES modification of the NACA 63A-108 airfoil Max thickness 7.7% at 30% chord Max camber 0.5% at 12.5% chord | Remove Airfoil details Airfoil plotter |
(joukowsk-il) 12% JOUKOWSKI AIRFOIL | 12% Joukowski airfoil Max thickness 11.8% at 25% chord Max camber 0% at 9.5% chord | Remove Airfoil details Airfoil plotter |
(e1212mod-il) EPPLER E1212MOD AIRFOIL | Eppler E1212 general aviation airfoil (as modified for use as Quickie wing airfoil) Max thickness 17.7% at 20.1% chord Max camber 2.6% at 35.1% chord | Remove Airfoil details Airfoil plotter |
(whitcomb-il) WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL | NASA/Langley Whitcomb integral supercritical airfoil Max thickness 11% at 35% chord Max camber 2.4% at 82.5% chord | Remove Airfoil details Airfoil plotter |
(lwk79100-il) LWK 79-100 | LWK 79-100 symmetrical airfoil Max thickness 10% at 27.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(ls421mod-il) NASA/LANGLEY LS(1)-0421MOD AIRFOIL | NASA/Langley LS(1)-0421MOD general aviation airfoil Max thickness 21% at 32.5% chord Max camber 2.3% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (a63a108c-il,joukowsk-il,e1212mod-il,whitcomb-il,lwk79100-il,ls421mod-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| a63a108c-il | 50,000 | 9 | 24.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a63a108c-il | 50,000 | 5 | 22.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a63a108c-il | 100,000 | 9 | 31.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a63a108c-il | 100,000 | 5 | 31.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a63a108c-il | 200,000 | 9 | 37.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a63a108c-il | 200,000 | 5 | 41.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a63a108c-il | 500,000 | 9 | 54.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a63a108c-il | 500,000 | 5 | 58.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a63a108c-il | 1,000,000 | 9 | 69.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a63a108c-il | 1,000,000 | 5 | 72.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk-il | 50,000 | 9 | 22.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk-il | 50,000 | 5 | 26.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk-il | 100,000 | 9 | 34.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk-il | 100,000 | 5 | 37.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk-il | 200,000 | 9 | 47.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk-il | 200,000 | 5 | 48.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk-il | 500,000 | 9 | 65.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk-il | 500,000 | 5 | 65.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk-il | 1,000,000 | 9 | 80.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk-il | 1,000,000 | 5 | 79.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212mod-il | 50,000 | 9 | 5.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 50,000 | 5 | 20.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212mod-il | 100,000 | 9 | 28 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 100,000 | 5 | 39.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212mod-il | 200,000 | 9 | 51.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 200,000 | 5 | 57.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212mod-il | 500,000 | 9 | 81.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 500,000 | 5 | 84.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212mod-il | 1,000,000 | 9 | 108.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 1,000,000 | 5 | 107.6 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| whitcomb-il | 50,000 | 9 | 22.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| whitcomb-il | 50,000 | 5 | 19.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| whitcomb-il | 100,000 | 9 | 22.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| whitcomb-il | 100,000 | 5 | 27.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| whitcomb-il | 200,000 | 9 | 30.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| whitcomb-il | 200,000 | 5 | 39.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| whitcomb-il | 500,000 | 9 | 49.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| whitcomb-il | 500,000 | 5 | 59.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| whitcomb-il | 1,000,000 | 9 | 69 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| whitcomb-il | 1,000,000 | 5 | 76.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 50,000 | 9 | 25.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 50,000 | 5 | 27.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 100,000 | 9 | 37.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 100,000 | 5 | 35.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 200,000 | 9 | 47.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 200,000 | 5 | 44.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 500,000 | 9 | 59.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 500,000 | 5 | 60.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 1,000,000 | 9 | 72.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 1,000,000 | 5 | 74.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421mod-il | 50,000 | 9 | 7.2 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421mod-il | 50,000 | 5 | 18.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421mod-il | 100,000 | 9 | 37.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421mod-il | 100,000 | 5 | 38.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421mod-il | 200,000 | 9 | 51.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421mod-il | 200,000 | 5 | 56 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421mod-il | 500,000 | 9 | 80.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421mod-il | 500,000 | 5 | 77.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421mod-il | 1,000,000 | 9 | 100 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421mod-il | 1,000,000 | 5 | 90.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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