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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(j5012-il) J5012 12% | Jef Raskin (originator of the Apple Macintosh Project) J5012 airfoil Max thickness 12% at 34.5% chord Max camber 0% at 83.5% chord | Remove Airfoil details Airfoil plotter |
(ultimate-il) ULTIMATE | Carl Goldberg R/C Ultimate Bipe airfoil Max thickness 12.8% at 34.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(m27-il) NACA M27 AIRFOIL | NACA/Munk M-27 airfoil Max thickness 12% at 30.1% chord Max camber 8.4% at 30.1% chord | Remove Airfoil details Airfoil plotter |
(s1048-il) S1048 14% (Danny Howell) | Selig S1048 airfoil Max thickness 14% at 27% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (j5012-il,ultimate-il,m27-il,s1048-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| j5012-il | 50,000 | 9 | 29 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| j5012-il | 50,000 | 5 | 28.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| j5012-il | 100,000 | 9 | 41.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| j5012-il | 100,000 | 5 | 38.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| j5012-il | 200,000 | 9 | 51.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| j5012-il | 200,000 | 5 | 45.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| j5012-il | 500,000 | 9 | 59.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| j5012-il | 500,000 | 5 | 58.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| j5012-il | 1,000,000 | 9 | 70.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| j5012-il | 1,000,000 | 5 | 70.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 50,000 | 9 | 28.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 50,000 | 5 | 27.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 100,000 | 9 | 39 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 100,000 | 5 | 36.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 200,000 | 9 | 47.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 200,000 | 5 | 42 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 500,000 | 9 | 55.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 500,000 | 5 | 53.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 1,000,000 | 9 | 63.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 1,000,000 | 5 | 67 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m27-il | 50,000 | 9 | 4.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m27-il | 50,000 | 5 | 9.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m27-il | 100,000 | 9 | 9 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m27-il | 100,000 | 5 | 41.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m27-il | 200,000 | 9 | 62.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m27-il | 200,000 | 5 | 70.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m27-il | 500,000 | 9 | 105.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m27-il | 500,000 | 5 | 105 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m27-il | 1,000,000 | 9 | 135.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m27-il | 1,000,000 | 5 | 126.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1048-il | 50,000 | 9 | 24.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1048-il | 50,000 | 5 | 28.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1048-il | 100,000 | 9 | 40.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1048-il | 100,000 | 5 | 41.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1048-il | 200,000 | 9 | 56 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1048-il | 200,000 | 5 | 54.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1048-il | 500,000 | 9 | 75.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1048-il | 500,000 | 5 | 66.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1048-il | 1,000,000 | 9 | 83.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1048-il | 1,000,000 | 5 | 72.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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