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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(geminism-il) GEMINI (smoothed) | GEMINI R/C sailplane airfoil (smoothed) Max thickness 15.4% at 34.2% chord Max camber 2.2% at 37.9% chord | Remove Airfoil details Airfoil plotter |
(sa7035-il) SA7035 | Selig / Ashok Gopalarathnam SA7035 Max thickness 9.2% at 27.9% chord Max camber 2.4% at 41.9% chord | Remove Airfoil details Airfoil plotter |
(goe406-il) GOE 406 AIRFOIL | Gottingen 406 airfoil Max thickness 11.7% at 29.9% chord Max camber 5.5% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(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 |
(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 |
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Polars for (geminism-il,sa7035-il,goe406-il,mh23-il,mh200-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| geminism-il | 50,000 | 9 | 8.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 50,000 | 5 | 28.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| geminism-il | 100,000 | 9 | 47.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 100,000 | 5 | 48.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| geminism-il | 200,000 | 9 | 66.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 200,000 | 5 | 65.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| geminism-il | 500,000 | 9 | 92.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 500,000 | 5 | 86.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| geminism-il | 1,000,000 | 9 | 110.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 1,000,000 | 5 | 100.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7035-il | 50,000 | 9 | 33.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7035-il | 50,000 | 5 | 37.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7035-il | 100,000 | 9 | 52.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7035-il | 100,000 | 5 | 53.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7035-il | 200,000 | 9 | 71.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7035-il | 200,000 | 5 | 68 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7035-il | 500,000 | 9 | 94.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7035-il | 500,000 | 5 | 87.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7035-il | 1,000,000 | 9 | 111.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7035-il | 1,000,000 | 5 | 101.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe406-il | 50,000 | 9 | 17.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 50,000 | 5 | 34.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe406-il | 100,000 | 9 | 54.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 100,000 | 5 | 53.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe406-il | 200,000 | 9 | 75.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 200,000 | 5 | 68.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe406-il | 500,000 | 9 | 94.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 500,000 | 5 | 89.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe406-il | 1,000,000 | 9 | 114.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 1,000,000 | 5 | 112 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| 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 | |
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