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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(sc20010-il) NASA SC(2)-0010 AIRFOIL | NASA SC(2)-0010 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe494-il) GOE 494 AIRFOIL | Gottingen 494 airfoil Max thickness 5% at 20% chord Max camber 5.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(aquilasm-il) AQUILA 9.3% smoothed | AQUILA R/C sailplane airfoil Max thickness 9.4% at 31.3% chord Max camber 4% at 34.7% 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 |
(mh95-il) MH 95 15.86% | Martin Hepperle MH 95 parafoil Max thickness 15.8% at 33.6% chord Max camber 0.9% at 81.6% chord | Remove Airfoil details Airfoil plotter |
(eiffel428-il) Eiffel 428 (Bleriot) | Eiffel 428 (Bleriot) airfoil Max thickness 9% at 30% chord Max camber 4.2% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe501-il) GOE 501 AIRFOIL | Gottingen 501 airfoil Max thickness 12.8% at 30% chord Max camber 6.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sc20010-il,goe494-il,aquilasm-il,mh23-il,mh95-il,eiffel428-il,goe501-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc20010-il | 50,000 | 9 | 23.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 50,000 | 5 | 22.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 100,000 | 9 | 33.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 100,000 | 5 | 28.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 200,000 | 9 | 39.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 200,000 | 5 | 39 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 500,000 | 9 | 52 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 500,000 | 5 | 56.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 1,000,000 | 9 | 67.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 1,000,000 | 5 | 70.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 50,000 | 9 | 44.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 50,000 | 5 | 45.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 100,000 | 9 | 69.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 100,000 | 5 | 69.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 200,000 | 9 | 97 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 200,000 | 5 | 95.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 500,000 | 9 | 135.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 500,000 | 5 | 121.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 1,000,000 | 9 | 164.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 1,000,000 | 5 | 112.3 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| aquilasm-il | 50,000 | 9 | 25.3 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 50,000 | 5 | 37 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| aquilasm-il | 100,000 | 9 | 51.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 100,000 | 5 | 56.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| aquilasm-il | 200,000 | 9 | 74.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 200,000 | 5 | 75 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| aquilasm-il | 500,000 | 9 | 104.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 500,000 | 5 | 99.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| aquilasm-il | 1,000,000 | 9 | 127.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 1,000,000 | 5 | 118.5 at α=6° | 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 | |
| mh95-il | 50,000 | 9 | 29.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh95-il | 50,000 | 5 | 29 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh95-il | 100,000 | 9 | 44.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh95-il | 100,000 | 5 | 37.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh95-il | 200,000 | 9 | 48.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh95-il | 200,000 | 5 | 45.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh95-il | 500,000 | 9 | 62.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh95-il | 500,000 | 5 | 60.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh95-il | 1,000,000 | 9 | 78 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh95-il | 1,000,000 | 5 | 74.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel428-il | 50,000 | 9 | 38.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel428-il | 50,000 | 5 | 38.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel428-il | 100,000 | 9 | 59.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel428-il | 100,000 | 5 | 50.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel428-il | 200,000 | 9 | 67.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel428-il | 200,000 | 5 | 54.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel428-il | 500,000 | 9 | 70.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel428-il | 500,000 | 5 | 68 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel428-il | 1,000,000 | 9 | 81.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel428-il | 1,000,000 | 5 | 84 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe501-il | 50,000 | 9 | 9.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe501-il | 50,000 | 5 | 29.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe501-il | 100,000 | 9 | 56.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe501-il | 100,000 | 5 | 60.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe501-il | 200,000 | 9 | 85.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe501-il | 200,000 | 5 | 80.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe501-il | 500,000 | 9 | 113.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe501-il | 500,000 | 5 | 106.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe501-il | 1,000,000 | 9 | 137.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe501-il | 1,000,000 | 5 | 113.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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