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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(ls421-il) NASA/LANGLEY LS(1)-0421 AIRFOIL | NASA/Langley LS(1)-0421 general aviation airfoil Max thickness 20.9% at 40% chord Max camber 2.4% at 65% chord | Remove Airfoil details Airfoil plotter |
(p51htip-il) NACA 66 | NACA 66 Max thickness 12% at 45% chord Max camber 1.3% at 47.5% chord | Remove Airfoil details Airfoil plotter |
(oa213-il) ONERA OA213 AIRFOIL | ONERA/Aerospatiale OA213 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 12.6% at 32.5% chord Max camber 3.3% at 25% chord | Remove Airfoil details Airfoil plotter |
(s2048-il) S2048 | Selig S2048 low Reynolds number airfoil Max thickness 8.6% at 35.4% chord Max camber 1.7% at 60.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ls421-il,p51htip-il,oa213-il,s2048-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ls421-il | 50,000 | 9 | 23.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 50,000 | 5 | 18.4 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421-il | 100,000 | 9 | 33.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 100,000 | 5 | 30.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421-il | 200,000 | 9 | 52.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 200,000 | 5 | 56.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421-il | 500,000 | 9 | 89.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 500,000 | 5 | 81.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421-il | 1,000,000 | 9 | 111.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 1,000,000 | 5 | 91.2 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51htip-il | 50,000 | 9 | 22.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51htip-il | 50,000 | 5 | 22.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51htip-il | 100,000 | 9 | 35.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51htip-il | 100,000 | 5 | 38.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51htip-il | 200,000 | 9 | 52.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51htip-il | 200,000 | 5 | 48 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51htip-il | 500,000 | 9 | 72.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51htip-il | 500,000 | 5 | 67 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51htip-il | 1,000,000 | 9 | 90.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51htip-il | 1,000,000 | 5 | 75.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 50,000 | 9 | 26.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 50,000 | 5 | 29.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 100,000 | 9 | 41.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 100,000 | 5 | 41.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 200,000 | 9 | 54 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 200,000 | 5 | 54.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 500,000 | 9 | 75.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 500,000 | 5 | 75.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 1,000,000 | 9 | 95.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 1,000,000 | 5 | 93.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2048-il | 50,000 | 9 | 37.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2048-il | 50,000 | 5 | 37.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2048-il | 100,000 | 9 | 55.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2048-il | 100,000 | 5 | 52.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2048-il | 200,000 | 9 | 75.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2048-il | 200,000 | 5 | 67.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2048-il | 500,000 | 9 | 100.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2048-il | 500,000 | 5 | 78.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2048-il | 1,000,000 | 9 | 110.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2048-il | 1,000,000 | 5 | 88.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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