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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(nacam3-il) NACA M3 | NACA M3 airfoil Max thickness 11.9% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe228-il) GOE 228 (MVA H.38) AIRFOIL | Gottingen 228 (MVA H.38) airfoil Max thickness 17.9% at 29.4% chord Max camber 7% at 49.4% 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 (nacam3-il,goe228-il,chen-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nacam3-il | 50,000 | 9 | 27.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 50,000 | 5 | 26.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 100,000 | 9 | 37.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 100,000 | 5 | 34.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 200,000 | 9 | 45.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 200,000 | 5 | 42.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 500,000 | 9 | 54.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 500,000 | 5 | 56.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 1,000,000 | 9 | 66.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 1,000,000 | 5 | 69.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe228-il | 50,000 | 9 | 5.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 50,000 | 5 | 25.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe228-il | 100,000 | 9 | 45.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 100,000 | 5 | 51.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe228-il | 200,000 | 9 | 70.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 200,000 | 5 | 66.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe228-il | 500,000 | 9 | 92.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 500,000 | 5 | 88.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe228-il | 1,000,000 | 9 | 116.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 1,000,000 | 5 | 109 at α=5° | 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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