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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(giiim-il) GIII BL430 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35.2% chord Max camber 1.9% at 25.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (giiim-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiim-il | 50,000 | 9 | 29.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiim-il | 50,000 | 5 | 31.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiim-il | 100,000 | 9 | 43.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiim-il | 100,000 | 5 | 41.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiim-il | 200,000 | 9 | 56.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiim-il | 200,000 | 5 | 52.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiim-il | 500,000 | 9 | 70.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiim-il | 500,000 | 5 | 70.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiim-il | 1,000,000 | 9 | 85.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiim-il | 1,000,000 | 5 | 85.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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