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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(mh70-il) MH 70 11.08% | Martin Hepperle MH 70 for fying wing (full size) Max thickness 11.1% at 29.4% chord Max camber 3% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(e211-il) E211 (10.96%) | Eppler E211 low Reynolds number airfoil Max thickness 10.9% at 31.7% chord Max camber 2.2% at 65.7% chord | Remove Airfoil details Airfoil plotter |
(e853-il) EPPLER E853 AIRFOIL | Eppler E853 propeller airfoil Max thickness 11.6% at 37.1% chord Max camber 3.1% at 56.1% chord | Remove Airfoil details Airfoil plotter |
(clarym18-il) CLARK YM-18 AIRFOIL | CLARK YM18 airfoil Max thickness 18% at 29.6% chord Max camber 3.6% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(be50-il) BE50 (original) | Verbitsky BE50 free flight airfoil (original) Max thickness 7.3% at 25% chord Max camber 4.1% at 45% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh70-il,e211-il,e853-il,clarym18-il,be50-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh70-il | 50,000 | 9 | 27.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 50,000 | 5 | 35.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh70-il | 100,000 | 9 | 50.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 100,000 | 5 | 52.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh70-il | 200,000 | 9 | 70.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 200,000 | 5 | 67.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh70-il | 500,000 | 9 | 95 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 500,000 | 5 | 87.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh70-il | 1,000,000 | 9 | 112.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 1,000,000 | 5 | 103.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e211-il | 50,000 | 9 | 37.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e211-il | 50,000 | 5 | 39.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e211-il | 100,000 | 9 | 58.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e211-il | 100,000 | 5 | 57.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e211-il | 200,000 | 9 | 78.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e211-il | 200,000 | 5 | 74.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e211-il | 500,000 | 9 | 106.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e211-il | 500,000 | 5 | 91.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e211-il | 1,000,000 | 9 | 118.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e211-il | 1,000,000 | 5 | 100.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e853-il | 50,000 | 9 | 35.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 50,000 | 5 | 35.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e853-il | 100,000 | 9 | 60.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 100,000 | 5 | 59.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e853-il | 200,000 | 9 | 85.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 200,000 | 5 | 82.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e853-il | 500,000 | 9 | 120.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 500,000 | 5 | 103 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e853-il | 1,000,000 | 9 | 135.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 1,000,000 | 5 | 114.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 50,000 | 9 | 7.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 50,000 | 5 | 25.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 100,000 | 9 | 43.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 100,000 | 5 | 43.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 200,000 | 9 | 60.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 200,000 | 5 | 56 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 500,000 | 9 | 77.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 500,000 | 5 | 73.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 1,000,000 | 9 | 96.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 1,000,000 | 5 | 93.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50-il | 50,000 | 9 | 38.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 50,000 | 5 | 43.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50-il | 100,000 | 9 | 59.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 100,000 | 5 | 59.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50-il | 200,000 | 9 | 79.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 200,000 | 5 | 73.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50-il | 500,000 | 9 | 102.1 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 500,000 | 5 | 95.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50-il | 1,000,000 | 9 | 118.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 1,000,000 | 5 | 110.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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