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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(giiil-il) GIII BL387 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35.1% chord Max camber 1.6% at 25.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (giiil-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiil-il | 50,000 | 9 | 31.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 50,000 | 5 | 31.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 100,000 | 9 | 45 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 100,000 | 5 | 42.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 200,000 | 9 | 57.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 200,000 | 5 | 51.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 500,000 | 9 | 72.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 500,000 | 5 | 67.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 1,000,000 | 9 | 82 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 1,000,000 | 5 | 82.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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