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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(giiij-il) GIII BL332 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35% chord Max camber 1.4% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (giiij-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiij-il | 50,000 | 9 | 32.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 50,000 | 5 | 32.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiij-il | 100,000 | 9 | 46.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 100,000 | 5 | 43.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiij-il | 200,000 | 9 | 59.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 200,000 | 5 | 52.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiij-il | 500,000 | 9 | 73.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 500,000 | 5 | 65.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiij-il | 1,000,000 | 9 | 79.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 1,000,000 | 5 | 79.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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