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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(n2414-il) NACA 2414 | NACA 2414 airfoil Max thickness 14% at 29.5% chord Max camber 2% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(rae103-il) RAE 103 AIRFOIL | RAE 103 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(giiik-il) GIII BL369 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35% chord Max camber 1.5% at 25% chord | Remove Airfoil details Airfoil plotter |
(chen-il) CHEN AIRFOIL | University of Illinois at Urbana-Champaign / Chen high lift airfoil Max thickness 12.5% at 27.7% chord Max camber 7.8% at 25.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n2414-il,rae103-il,giiik-il,chen-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n2414-il | 50,000 | 9 | 29.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 50,000 | 5 | 32.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2414-il | 100,000 | 9 | 47.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 100,000 | 5 | 48.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2414-il | 200,000 | 9 | 65.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 200,000 | 5 | 62.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2414-il | 500,000 | 9 | 87.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 500,000 | 5 | 79.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2414-il | 1,000,000 | 9 | 103.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 1,000,000 | 5 | 90 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae103-il | 50,000 | 9 | 27.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 50,000 | 5 | 27.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae103-il | 100,000 | 9 | 40.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 100,000 | 5 | 36.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae103-il | 200,000 | 9 | 48.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 200,000 | 5 | 39.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae103-il | 500,000 | 9 | 54.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 500,000 | 5 | 52.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae103-il | 1,000,000 | 9 | 62.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 1,000,000 | 5 | 66 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiik-il | 50,000 | 9 | 32.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiik-il | 50,000 | 5 | 32 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiik-il | 100,000 | 9 | 45.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiik-il | 100,000 | 5 | 42.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiik-il | 200,000 | 9 | 58 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiik-il | 200,000 | 5 | 51.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiik-il | 500,000 | 9 | 72.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiik-il | 500,000 | 5 | 66.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiik-il | 1,000,000 | 9 | 79.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiik-il | 1,000,000 | 5 | 81.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 50,000 | 9 | 4.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 50,000 | 5 | 4.8 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 100,000 | 9 | 4.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 100,000 | 5 | 8.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 200,000 | 9 | 5.6 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 200,000 | 5 | 19.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 500,000 | 9 | 13.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 500,000 | 5 | 56.5 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 1,000,000 | 9 | 125.4 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 1,000,000 | 5 | 123 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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