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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(giiih-il) GIII BL207 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 39.9% chord Max camber 1.3% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(fx74130wp2-il) 74-130 WP2 | Wortmann 74-130 WP2 airfoil Max thickness 13% at 43.5% chord Max camber 3.9% at 46.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (giiih-il,fx74130wp2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiih-il | 50,000 | 9 | 33.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiih-il | 50,000 | 5 | 32.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiih-il | 100,000 | 9 | 47.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiih-il | 100,000 | 5 | 44.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiih-il | 200,000 | 9 | 62 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiih-il | 200,000 | 5 | 55.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiih-il | 500,000 | 9 | 78.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiih-il | 500,000 | 5 | 60.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiih-il | 1,000,000 | 9 | 82.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiih-il | 1,000,000 | 5 | 74.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp2-il | 50,000 | 9 | 23.1 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp2-il | 50,000 | 5 | 22.1 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp2-il | 100,000 | 9 | 37 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp2-il | 100,000 | 5 | 36.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp2-il | 200,000 | 9 | 72.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp2-il | 200,000 | 5 | 75.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp2-il | 500,000 | 9 | 125.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp2-il | 500,000 | 5 | 119.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp2-il | 1,000,000 | 9 | 161.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp2-il | 1,000,000 | 5 | 150.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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