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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(giiib-il) GIII BL45 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 10.4% at 39.7% chord Max camber 0.8% at 24.7% chord | Remove Airfoil details Airfoil plotter |
(giiif-il) GIII BL145 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 44.9% chord Max camber 1.3% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (giiib-il,giiif-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiib-il | 50,000 | 9 | 28.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiib-il | 50,000 | 5 | 29.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiib-il | 100,000 | 9 | 41.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiib-il | 100,000 | 5 | 39.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiib-il | 200,000 | 9 | 52.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiib-il | 200,000 | 5 | 50.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiib-il | 500,000 | 9 | 68.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiib-il | 500,000 | 5 | 61.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiib-il | 1,000,000 | 9 | 76.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiib-il | 1,000,000 | 5 | 70.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiif-il | 50,000 | 9 | 32.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiif-il | 50,000 | 5 | 32.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiif-il | 100,000 | 9 | 46.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiif-il | 100,000 | 5 | 44.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiif-il | 200,000 | 9 | 61.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiif-il | 200,000 | 5 | 55.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiif-il | 500,000 | 9 | 78.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiif-il | 500,000 | 5 | 62.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiif-il | 1,000,000 | 9 | 83.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiif-il | 1,000,000 | 5 | 72.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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