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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(mh23-il) MH 23 8% | Martin Hepperle MH 23 for F3D Pylon Racing (extended laminar flow) Max thickness 8% at 37.5% chord Max camber 1.2% at 42.7% chord | Remove Airfoil details Airfoil plotter |
(mh91-il) MH 91 14.98% | Martin Hepperle MH 91 parafoil Max thickness 15% at 27.3% chord Max camber 1.4% at 18.7% chord | Remove Airfoil details Airfoil plotter |
(n63210-il) NACA 63-210 AIRFOIL | NACA 63-210 airfoil Max thickness 10% at 35% chord Max camber 1.1% at 60% chord | Remove Airfoil details Airfoil plotter |
(mh150-il) MH 150 23.89% | Martin Hepperle MH 150 for marine ruddershaft for torque reduction (schottel units) Max thickness 23.9% at 27.2% chord Max camber 4.5% at 53.8% chord | Remove Airfoil details Airfoil plotter |
(mh44-il) MH 44 9.66% | Martin Hepperle MH 44 for flying wings Max thickness 9.6% at 27.1% chord Max camber 1.5% at 36.9% chord | Remove Airfoil details Airfoil plotter |
(mh200-il) MH 200 12.97% | Martin Hepperle MH 200 for a canard airplane (main wing) Max thickness 13% at 39.5% chord Max camber 2.1% at 49.8% chord | Remove Airfoil details Airfoil plotter |
(mh104-il) MH 104 15.28% | Martin Hepperle MH 104 for stall controlled wind turbines Max thickness 15.2% at 26.4% chord Max camber 1.9% at 31.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh23-il,mh91-il,n63210-il,mh150-il,mh44-il,mh200-il,mh104-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh23-il | 50,000 | 9 | 34.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh23-il | 50,000 | 5 | 33.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh23-il | 100,000 | 9 | 50 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh23-il | 100,000 | 5 | 45.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh23-il | 200,000 | 9 | 66.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh23-il | 200,000 | 5 | 57.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh23-il | 500,000 | 9 | 83.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh23-il | 500,000 | 5 | 66.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh23-il | 1,000,000 | 9 | 83.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh23-il | 1,000,000 | 5 | 72.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh91-il | 50,000 | 9 | 16.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 50,000 | 5 | 25.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh91-il | 100,000 | 9 | 34.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 100,000 | 5 | 40.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh91-il | 200,000 | 9 | 52.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 200,000 | 5 | 55.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh91-il | 500,000 | 9 | 78.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 500,000 | 5 | 75.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh91-il | 1,000,000 | 9 | 96.6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 1,000,000 | 5 | 91.4 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 50,000 | 9 | 33.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 50,000 | 5 | 32 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 100,000 | 9 | 46.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 100,000 | 5 | 42.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 200,000 | 9 | 59.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 200,000 | 5 | 48.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 500,000 | 9 | 67.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 500,000 | 5 | 55.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 1,000,000 | 9 | 69 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 1,000,000 | 5 | 66.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh150-il | 50,000 | 9 | 3.9 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh150-il | 50,000 | 5 | 7.8 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh150-il | 100,000 | 9 | 14.2 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh150-il | 100,000 | 5 | 38.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh150-il | 200,000 | 9 | 56.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh150-il | 200,000 | 5 | 61.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh150-il | 500,000 | 9 | 90.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh150-il | 500,000 | 5 | 88.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh150-il | 1,000,000 | 9 | 117.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh150-il | 1,000,000 | 5 | 112.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh44-il | 50,000 | 9 | 29.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh44-il | 50,000 | 5 | 32.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh44-il | 100,000 | 9 | 44.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh44-il | 100,000 | 5 | 45.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh44-il | 200,000 | 9 | 60.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh44-il | 200,000 | 5 | 58.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh44-il | 500,000 | 9 | 80.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh44-il | 500,000 | 5 | 74.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh44-il | 1,000,000 | 9 | 94.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh44-il | 1,000,000 | 5 | 87.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 50,000 | 9 | 33.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 50,000 | 5 | 32.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 100,000 | 9 | 53.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 100,000 | 5 | 51 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 200,000 | 9 | 76.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 200,000 | 5 | 66.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 500,000 | 9 | 98.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 500,000 | 5 | 85.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 1,000,000 | 9 | 117 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 1,000,000 | 5 | 93.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 50,000 | 9 | 12 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 50,000 | 5 | 21.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 100,000 | 9 | 37.2 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 100,000 | 5 | 43.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 200,000 | 9 | 62.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 200,000 | 5 | 65 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 500,000 | 9 | 95.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 500,000 | 5 | 92.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 1,000,000 | 9 | 120.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 1,000,000 | 5 | 106.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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