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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(giiid-il) GIII BL86 AIRFOIL (modified line 31) | Grumman/Gulfstream GIII transonic airfoils Max thickness 9.7% at 39.8% chord Max camber 1% at 29.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (giiid-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiid-il | 50,000 | 9 | 31 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiid-il | 100,000 | 9 | 45.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiid-il | 200,000 | 9 | 59.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiid-il | 500,000 | 9 | 70.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiid-il | 1,000,000 | 9 | 75.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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