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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(giiin-il) GIII BL450 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.4% at 30.2% chord Max camber 2.1% at 20.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (giiin-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiin-il | 50,000 | 9 | 28.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiin-il | 50,000 | 5 | 30.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiin-il | 100,000 | 9 | 41.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiin-il | 100,000 | 5 | 40.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiin-il | 200,000 | 9 | 54.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiin-il | 200,000 | 5 | 53 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiin-il | 500,000 | 9 | 70.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiin-il | 500,000 | 5 | 71.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiin-il | 1,000,000 | 9 | 87.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiin-il | 1,000,000 | 5 | 87.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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