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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(mh45-il) MH 45 9.85% | Martin Hepperle MH 45 for flying wings Max thickness 9.8% at 26.9% chord Max camber 1.7% at 36.6% chord | Remove Airfoil details Airfoil plotter |
(mh61-il) MH 61 10.26% | Martin Hepperle MH 61 for flying wings Max thickness 10.2% at 27.6% chord Max camber 1.4% at 37.3% chord | Remove Airfoil details Airfoil plotter |
(mh32-il) MH 32 8.7% | Martin Hepperle MH 32 for F3E and F3B Max thickness 8.7% at 30.2% chord Max camber 2.3% at 45.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh45-il,mh61-il,mh32-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh45-il | 50,000 | 9 | 27.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 50,000 | 5 | 32.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 100,000 | 9 | 44.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 100,000 | 5 | 45.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 200,000 | 9 | 60.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 200,000 | 5 | 58.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 500,000 | 9 | 81.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 500,000 | 5 | 75.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 1,000,000 | 9 | 95.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 1,000,000 | 5 | 88.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh61-il | 50,000 | 9 | 31.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 50,000 | 5 | 33 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh61-il | 100,000 | 9 | 47.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 100,000 | 5 | 47.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh61-il | 200,000 | 9 | 63.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 200,000 | 5 | 60.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh61-il | 500,000 | 9 | 84.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 500,000 | 5 | 76.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh61-il | 1,000,000 | 9 | 98 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 1,000,000 | 5 | 86.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh32-il | 50,000 | 9 | 35.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 50,000 | 5 | 37.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh32-il | 100,000 | 9 | 53.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 100,000 | 5 | 53.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh32-il | 200,000 | 9 | 72.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 200,000 | 5 | 67.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh32-il | 500,000 | 9 | 94.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 500,000 | 5 | 84 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh32-il | 1,000,000 | 9 | 109.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 1,000,000 | 5 | 96.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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