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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(giiie-il) GIII BL126 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.8% at 44.9% chord Max camber 1.2% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (giiie-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiie-il | 50,000 | 9 | 32.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiie-il | 50,000 | 5 | 32.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiie-il | 100,000 | 9 | 47.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiie-il | 100,000 | 5 | 44.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiie-il | 200,000 | 9 | 61.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiie-il | 200,000 | 5 | 55.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiie-il | 500,000 | 9 | 76.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiie-il | 500,000 | 5 | 60.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiie-il | 1,000,000 | 9 | 81.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiie-il | 1,000,000 | 5 | 72.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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