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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(m6-il) NACA M6 AIRFOIL | NACA/Munk M-6 airfoil Max thickness 12% at 30% chord Max camber 2.2% at 30% chord | Remove Airfoil details Airfoil plotter |
(raf48-il) RAF-48 AIRFOIL | RAF-48 airfoil Max thickness 15% at 30% chord Max camber 2.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(m12-il) NACA M12 AIRFOIL | NACA/Munk M-12 airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord | Remove Airfoil details Airfoil plotter |
(m15-il) NACA M15 AIRFOIL | NACA/Munk M-15 airfoil Max thickness 12% at 30% chord Max camber 3.8% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe255-il) GOE 255 (MVA CA.6) AIRFOIL | Gottingen 255 (MVA CA.6) airfoil Max thickness 18.5% at 29.1% chord Max camber 4.8% at 49.1% chord | Remove Airfoil details Airfoil plotter |
(clarkk-il) CLARK K AIRFOIL | CLARK K airfoil Max thickness 11.7% at 29.7% chord Max camber 3.3% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(goe679-il) GOE 679 AIRFOIL | Gottingen 679 airfoil Max thickness 18.3% at 29.1% chord Max camber 4.5% at 39.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m6-il,raf48-il,m12-il,m15-il,goe255-il,clarkk-il,goe679-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m6-il | 50,000 | 9 | 30.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m6-il | 50,000 | 5 | 32 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m6-il | 100,000 | 9 | 48.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m6-il | 100,000 | 5 | 48.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m6-il | 200,000 | 9 | 66.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m6-il | 200,000 | 5 | 63.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m6-il | 500,000 | 9 | 87.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m6-il | 500,000 | 5 | 76.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m6-il | 1,000,000 | 9 | 97 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m6-il | 1,000,000 | 5 | 83.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 50,000 | 9 | 7.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 50,000 | 5 | 25.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 100,000 | 9 | 45.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 100,000 | 5 | 49.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 200,000 | 9 | 68.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 200,000 | 5 | 67.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 500,000 | 9 | 97.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 500,000 | 5 | 93.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 1,000,000 | 9 | 121.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 1,000,000 | 5 | 108.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 50,000 | 9 | 31.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 50,000 | 5 | 33.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 100,000 | 9 | 49 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 100,000 | 5 | 48.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 200,000 | 9 | 65.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 200,000 | 5 | 62.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 500,000 | 9 | 86.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 500,000 | 5 | 77.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 1,000,000 | 9 | 98.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 1,000,000 | 5 | 85.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 50,000 | 9 | 23.8 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 50,000 | 5 | 30 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 100,000 | 9 | 50.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 100,000 | 5 | 53.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 200,000 | 9 | 72.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 200,000 | 5 | 72.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 500,000 | 9 | 101.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 500,000 | 5 | 98.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 1,000,000 | 9 | 124.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 1,000,000 | 5 | 118.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 50,000 | 9 | 5.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 50,000 | 5 | 15.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 100,000 | 9 | 41.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 100,000 | 5 | 47.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 200,000 | 9 | 72.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 200,000 | 5 | 71.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 500,000 | 9 | 105.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 500,000 | 5 | 90.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 1,000,000 | 9 | 127.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 1,000,000 | 5 | 96.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 50,000 | 9 | 32.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 50,000 | 5 | 36.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 100,000 | 9 | 54.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 100,000 | 5 | 54.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 200,000 | 9 | 75.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 200,000 | 5 | 71.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 500,000 | 9 | 102.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 500,000 | 5 | 91.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 1,000,000 | 9 | 121.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 1,000,000 | 5 | 104.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe679-il | 50,000 | 9 | 5.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 50,000 | 5 | 25.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe679-il | 100,000 | 9 | 42.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 100,000 | 5 | 41.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe679-il | 200,000 | 9 | 58.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 200,000 | 5 | 54.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe679-il | 500,000 | 9 | 76.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 500,000 | 5 | 72.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe679-il | 1,000,000 | 9 | 95.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 1,000,000 | 5 | 88.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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