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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(ua79sfm-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT | University of Alberta/Marsden UA 79-SF-187 sailplane airfoil MAIN ELEMENT Max thickness 18.8% at 42.8% chord Max camber 3% at 66.9% chord | Remove Airfoil details Airfoil plotter |
(naca66210-il) NACA 66-210 | NACA 66-210 airfoil Max thickness 10% at 45% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe167-il) GOE 167 (V.KARMAN PROP.2) AIRFOIL | Gottingen 167 (V.Karman PROP.2) airfoil Max thickness 10.1% at 29.9% chord Max camber 4.5% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(mh122-il) MH 122 9.32% | Martin Hepperle MH 122 for tip section of a propeller Max thickness 9.3% at 37.6% chord Max camber 3.4% at 64.3% chord | Remove Airfoil details Airfoil plotter |
(goe484-il) GOE 484 AIRFOIL | Gottingen 484 airfoil Max thickness 6.3% at 30% chord Max camber 5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ua79sfm-il,naca66210-il,goe167-il,mh122-il,goe484-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ua79sfm-il | 50,000 | 9 | 12.2 at α=17.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 50,000 | 5 | 16.3 at α=14.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sfm-il | 100,000 | 9 | 41.3 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 100,000 | 5 | 40.2 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sfm-il | 200,000 | 9 | 82.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 200,000 | 5 | 80 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sfm-il | 500,000 | 9 | 145.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 500,000 | 5 | 142.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sfm-il | 1,000,000 | 9 | 291 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 1,000,000 | 5 | 241.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 50,000 | 9 | 22.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 50,000 | 5 | 27.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 100,000 | 9 | 32.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 100,000 | 5 | 36.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 200,000 | 9 | 51.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 200,000 | 5 | 46.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 500,000 | 5 | 61.9 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 500,000 | 0 | 67.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 1,000,000 | 9 | 82.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 1,000,000 | 5 | 67.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe167-il | 50,000 | 9 | 26.6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe167-il | 50,000 | 5 | 34 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe167-il | 100,000 | 9 | 58 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe167-il | 100,000 | 5 | 58.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe167-il | 200,000 | 9 | 80.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe167-il | 200,000 | 5 | 78.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe167-il | 500,000 | 9 | 106.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe167-il | 500,000 | 5 | 97.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe167-il | 1,000,000 | 9 | 124.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe167-il | 1,000,000 | 5 | 108.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 50,000 | 9 | 38 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 50,000 | 5 | 38 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 100,000 | 9 | 61.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 100,000 | 5 | 58.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 200,000 | 9 | 90.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 200,000 | 5 | 87.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 500,000 | 9 | 137.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 500,000 | 5 | 114.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 1,000,000 | 9 | 161.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 1,000,000 | 5 | 125.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe484-il | 50,000 | 9 | 45 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe484-il | 50,000 | 5 | 44.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe484-il | 100,000 | 9 | 67.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe484-il | 100,000 | 5 | 65.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe484-il | 200,000 | 9 | 93.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe484-il | 200,000 | 5 | 86.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe484-il | 500,000 | 9 | 128 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe484-il | 500,000 | 5 | 93.4 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe484-il | 1,000,000 | 9 | 136.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe484-il | 1,000,000 | 5 | 92.7 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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