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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(mrc-16-il) MRC-16 | Drela MRC-16 Max thickness 13.9% at 34.6% chord Max camber 3% at 40.3% chord | Remove Airfoil details Airfoil plotter |
(rg15-il) RG-15 8.9% | Rolf Girsberger RG 15 low Reynolds number airfoil Max thickness 8.9% at 30.2% chord Max camber 1.8% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(mh102-il) MH 102 16.99% | Martin Hepperle MH 102 for stall controlled wind turbines (root) Max thickness 17% at 27.7% chord Max camber 2.8% at 37.6% chord | Remove Airfoil details Airfoil plotter |
(sc20010-il) NASA SC(2)-0010 AIRFOIL | NASA SC(2)-0010 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mrc-16-il,rg15-il,mh102-il,sc20010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mrc-16-il | 50,000 | 9 | 23.1 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-16-il | 50,000 | 5 | 31.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-16-il | 100,000 | 9 | 50.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-16-il | 100,000 | 5 | 52.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-16-il | 200,000 | 9 | 73.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-16-il | 200,000 | 5 | 71.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-16-il | 500,000 | 9 | 102.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-16-il | 500,000 | 5 | 94.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-16-il | 1,000,000 | 9 | 124.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-16-il | 1,000,000 | 5 | 110.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15-il | 50,000 | 9 | 34.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 50,000 | 5 | 36.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15-il | 100,000 | 9 | 52.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 100,000 | 5 | 50.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15-il | 200,000 | 9 | 68.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 200,000 | 5 | 63.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15-il | 500,000 | 9 | 89 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 500,000 | 5 | 79 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15-il | 1,000,000 | 9 | 102.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 1,000,000 | 5 | 88.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh102-il | 50,000 | 9 | 5.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh102-il | 50,000 | 5 | 23.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh102-il | 100,000 | 9 | 37.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh102-il | 100,000 | 5 | 45.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh102-il | 200,000 | 9 | 63.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh102-il | 200,000 | 5 | 65.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh102-il | 500,000 | 9 | 94.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh102-il | 500,000 | 5 | 91 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh102-il | 1,000,000 | 9 | 118.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh102-il | 1,000,000 | 5 | 110.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 50,000 | 9 | 23.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 50,000 | 5 | 22.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 100,000 | 9 | 33.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 100,000 | 5 | 28.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 200,000 | 9 | 39.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 200,000 | 5 | 39 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 500,000 | 9 | 52 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 500,000 | 5 | 56.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 1,000,000 | 9 | 67.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 1,000,000 | 5 | 70.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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