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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(goe693-il) GOE 693 AIRFOIL | Gottingen 693 airfoil Max thickness 12% at 30% chord Max camber 3.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(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 |
(goe479-il) GOE 479 AIRFOIL | Gottingen 479 airfoil Max thickness 11.6% at 30% chord Max camber 4% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe693-il,l188root-il,goe479-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe693-il | 50,000 | 9 | 32.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe693-il | 50,000 | 5 | 35.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe693-il | 100,000 | 9 | 56 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe693-il | 100,000 | 5 | 55.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe693-il | 200,000 | 9 | 78.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe693-il | 200,000 | 5 | 72.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe693-il | 500,000 | 9 | 103.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe693-il | 500,000 | 5 | 87.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe693-il | 1,000,000 | 9 | 115.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe693-il | 1,000,000 | 5 | 97.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| goe479-il | 50,000 | 9 | 31.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe479-il | 50,000 | 5 | 35.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe479-il | 100,000 | 9 | 53.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe479-il | 100,000 | 5 | 55.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe479-il | 200,000 | 9 | 75.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe479-il | 200,000 | 5 | 72.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe479-il | 500,000 | 9 | 101.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe479-il | 500,000 | 5 | 94.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe479-il | 1,000,000 | 9 | 121.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe479-il | 1,000,000 | 5 | 110.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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