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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(mh108-il) MH 108 11.98% | Martin Hepperle MH 108 for stall controlled wind turbines Max thickness 11.9% at 22.8% chord Max camber 1% at 22.8% chord | Remove Airfoil details Airfoil plotter |
(n24-il) N-24 | N-24 airfoil Max thickness 17% at 30% chord Max camber 5.4% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe164-il) GOE 164 (MVA MK.10) AIRFOIL | Gottingen 164 (MVA MK.10) airfoil Max thickness 8.9% at 19.9% chord Max camber 6.6% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(n63015a-il) NACA 63-015A AIRFOIL | NACA 63-015A airfoil Max thickness 15% at 35% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(du84132v-il) DELFT DU84-132V3 AIRFOIL (MEASURED) | Airfoil measured from an ASW22 wing Max thickness 13.6% at 33.9% chord Max camber 3.1% at 45.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh108-il,n24-il,goe164-il,n63015a-il,du84132v-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh108-il | 50,000 | 9 | 16.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh108-il | 50,000 | 5 | 25.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh108-il | 100,000 | 9 | 36.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh108-il | 100,000 | 5 | 42.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh108-il | 200,000 | 9 | 56.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh108-il | 200,000 | 5 | 58.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh108-il | 500,000 | 9 | 82.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh108-il | 500,000 | 5 | 79.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh108-il | 1,000,000 | 9 | 102 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh108-il | 1,000,000 | 5 | 93.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n24-il | 50,000 | 9 | 6.5 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n24-il | 50,000 | 5 | 24.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n24-il | 100,000 | 9 | 41.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n24-il | 100,000 | 5 | 47 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n24-il | 200,000 | 9 | 65.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n24-il | 200,000 | 5 | 64.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n24-il | 500,000 | 9 | 91.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n24-il | 500,000 | 5 | 84.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n24-il | 1,000,000 | 9 | 108.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n24-il | 1,000,000 | 5 | 104.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe164-il | 50,000 | 9 | 34.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe164-il | 50,000 | 5 | 43.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe164-il | 100,000 | 9 | 60.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe164-il | 100,000 | 5 | 62.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe164-il | 200,000 | 9 | 81.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe164-il | 200,000 | 5 | 77.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe164-il | 500,000 | 9 | 104.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe164-il | 500,000 | 5 | 92 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe164-il | 1,000,000 | 9 | 112.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe164-il | 1,000,000 | 5 | 102.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63015a-il | 50,000 | 9 | 28.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63015a-il | 50,000 | 5 | 28.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63015a-il | 100,000 | 9 | 44.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63015a-il | 100,000 | 5 | 39.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63015a-il | 200,000 | 9 | 53.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63015a-il | 200,000 | 5 | 46.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63015a-il | 500,000 | 9 | 66.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63015a-il | 500,000 | 5 | 55.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63015a-il | 1,000,000 | 9 | 72.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63015a-il | 1,000,000 | 5 | 66.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du84132v-il | 50,000 | 9 | 31.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 50,000 | 5 | 34.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du84132v-il | 100,000 | 9 | 53.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 100,000 | 5 | 52.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du84132v-il | 200,000 | 9 | 71.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 200,000 | 5 | 62.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du84132v-il | 500,000 | 9 | 82 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 500,000 | 5 | 75.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du84132v-il | 1,000,000 | 9 | 92.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 1,000,000 | 5 | 82.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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