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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(l188root-il) LOCKHEED L-188 ROOT AIRFOIL | Lockheed L-188/P-3 root airfoil NACA 0014 -1.10 40/1.051 Cli=.3 a=.8 Max thickness 14% at 41.3% chord Max camber 2% at 51.7% chord | Remove Airfoil details Airfoil plotter |
(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 |
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Polars for (l188root-il,ls421-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| l188root-il | 50,000 | 9 | 32.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 50,000 | 5 | 29.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188root-il | 100,000 | 9 | 51.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 100,000 | 5 | 48.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188root-il | 200,000 | 9 | 72.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 200,000 | 5 | 65.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188root-il | 500,000 | 9 | 94.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 500,000 | 5 | 75.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188root-il | 1,000,000 | 9 | 104 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 1,000,000 | 5 | 79.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
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