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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(goe645-il) GOE 645 AIRFOIL | Gottingen 645 airfoil Max thickness 15.4% at 19.4% chord Max camber 4.8% at 39.4% chord | Remove Airfoil details Airfoil plotter |
(mh92-il) MH 92 15.49% | Martin Hepperle MH 92 parafoil Max thickness 15.5% at 27.4% chord Max camber 1.4% at 15.1% chord | Remove Airfoil details Airfoil plotter |
(goe134-il) GOE 134 (MVA H.12) AIRFOIL | Gottingen 134 (MVA H.12) airfoil Max thickness 9.5% at 30% chord Max camber 4% at 30% chord | Remove Airfoil details Airfoil plotter |
(cast102-il) CAST 10-2/DOA 2 AIRFOIL | CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe645-il,mh92-il,goe134-il,cast102-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe645-il | 50,000 | 9 | 9.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 50,000 | 5 | 28.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 100,000 | 9 | 43.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 100,000 | 5 | 48.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 200,000 | 9 | 66.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 200,000 | 5 | 65.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 500,000 | 9 | 93.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 500,000 | 5 | 84.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 1,000,000 | 9 | 110.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 1,000,000 | 5 | 88.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh92-il | 50,000 | 9 | 15.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 50,000 | 5 | 24.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh92-il | 100,000 | 9 | 33.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 100,000 | 5 | 40 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh92-il | 200,000 | 9 | 52.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 200,000 | 5 | 54.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh92-il | 500,000 | 9 | 76.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 500,000 | 5 | 73.4 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh92-il | 1,000,000 | 9 | 94.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 1,000,000 | 5 | 90.1 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 50,000 | 9 | 29.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 50,000 | 5 | 38.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 100,000 | 9 | 50.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 100,000 | 5 | 55.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 200,000 | 9 | 70.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 200,000 | 5 | 71.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 500,000 | 9 | 96.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 500,000 | 5 | 93.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 1,000,000 | 9 | 114.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 1,000,000 | 5 | 109.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 50,000 | 9 | 32.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 50,000 | 5 | 30.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 100,000 | 9 | 45.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 100,000 | 5 | 43 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 200,000 | 9 | 64 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 200,000 | 5 | 55.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 500,000 | 9 | 85.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 500,000 | 5 | 66.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 1,000,000 | 9 | 93.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 1,000,000 | 5 | 75.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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