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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(ua79sf18-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL | University of Alberta/Marsden UA 79-SF-187 FLAPPED sailplane airfoil Max thickness 18.8% at 42.8% chord Max camber 3.7% at 63.4% chord | Remove Airfoil details Airfoil plotter |
(fx05h126-il) WORTMANN FX 05-H-126 AIRFOIL | Wortmann FX 05-H-126 rotorcraft airfoil Max thickness 12.6% at 37.1% chord Max camber 4.4% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(v43012-il) BOEING VERTOL V43012-1.58 AIRFOIL | Boeing-Vertol V43012-1.58 rotorcraft airfoil Max thickness 12% at 32% chord Max camber 3.7% at 15% chord | Remove Airfoil details Airfoil plotter |
(naca23021-il) NACA 23021 | NACA 23021 airfoil Max thickness 21% at 30% chord Max camber 1.9% at 10% chord | Remove Airfoil details Airfoil plotter |
(boe106-il) BOEING 106 AIRFOIL | Boeing 106 airfoil Max thickness 13.1% at 30% chord Max camber 3.3% at 40% chord | Remove Airfoil details Airfoil plotter |
(daytonwright6-il) Dayton-Wright 6 | Dayton-Wright 6 airfoil Max thickness 13.6% at 30% chord Max camber 4.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(fx049915-il) WORTMANN FX 049-915 AIRFOIL | Wortmann FX 049-915 airfoil Max thickness 14.7% at 37.1% chord Max camber 5.8% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(v23010-il) BOEING-VERTOL V23010-1.58 AIRFOIL | Boeing-Vertol V23010-1.58 rotorcraft airfoil Max thickness 10.2% at 30% chord Max camber 1.8% at 15% chord | Remove Airfoil details Airfoil plotter |
(v43015-il) BOEING VERTOL V43015-2.48 AIRFOIL | Boeing-Vertol V43015-2.48 rotorcraft airfoil Max thickness 15% at 30% chord Max camber 3.7% at 15% chord | Remove Airfoil details Airfoil plotter |
(ua2-180sm-il) UA(2)-180 smoothed | UA(2)-180 (smoothed) airfoil for ultralight category aircraft Max thickness 18.2% at 34.1% chord Max camber 6.5% at 39.3% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (ua79sf18-il,fx05h126-il,v43012-il,naca23021-il,boe106-il,daytonwright6-il,fx049915-il,v23010-il,v43015-il,ua2-180sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ua79sf18-il | 50,000 | 9 | 15 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 50,000 | 5 | 15.2 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sf18-il | 100,000 | 9 | 24.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 100,000 | 5 | 23.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sf18-il | 200,000 | 9 | 37.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 200,000 | 5 | 35 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sf18-il | 500,000 | 9 | 65 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 500,000 | 5 | 75.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sf18-il | 1,000,000 | 9 | 133.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 1,000,000 | 5 | 114.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05h126-il | 50,000 | 9 | 19.1 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 50,000 | 5 | 14.5 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05h126-il | 100,000 | 9 | 25.1 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 100,000 | 5 | 24.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05h126-il | 200,000 | 9 | 66.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 200,000 | 5 | 70.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05h126-il | 500,000 | 9 | 121.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 500,000 | 5 | 116.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05h126-il | 1,000,000 | 9 | 158.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 1,000,000 | 5 | 145.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43012-il | 50,000 | 9 | 24 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 50,000 | 5 | 28.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43012-il | 100,000 | 9 | 36.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 100,000 | 5 | 40.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43012-il | 200,000 | 9 | 50.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 200,000 | 5 | 55.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43012-il | 500,000 | 9 | 77.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 500,000 | 5 | 81.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43012-il | 1,000,000 | 9 | 102.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 1,000,000 | 5 | 101.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23021-il | 50,000 | 9 | 18.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23021-il | 50,000 | 5 | 24.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23021-il | 100,000 | 9 | 37 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23021-il | 100,000 | 5 | 35.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23021-il | 200,000 | 9 | 49.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23021-il | 200,000 | 5 | 42.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23021-il | 500,000 | 9 | 56.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23021-il | 500,000 | 5 | 50.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23021-il | 1,000,000 | 9 | 64.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23021-il | 1,000,000 | 5 | 55.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe106-il | 50,000 | 9 | 29.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 50,000 | 5 | 32.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe106-il | 100,000 | 9 | 51.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 100,000 | 5 | 52.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe106-il | 200,000 | 9 | 72.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 200,000 | 5 | 70.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe106-il | 500,000 | 9 | 98.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 500,000 | 5 | 92 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe106-il | 1,000,000 | 9 | 118.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 1,000,000 | 5 | 108.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 50,000 | 9 | 11 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 50,000 | 5 | 31.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 100,000 | 9 | 45.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 100,000 | 5 | 49.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 200,000 | 9 | 66.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 200,000 | 5 | 66.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 500,000 | 9 | 92.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 500,000 | 5 | 89.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 1,000,000 | 9 | 115.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 1,000,000 | 5 | 111.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx049915-il | 50,000 | 9 | 4.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx049915-il | 50,000 | 5 | 10.4 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx049915-il | 100,000 | 9 | 6.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx049915-il | 100,000 | 5 | 24.1 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx049915-il | 200,000 | 9 | 25.4 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx049915-il | 200,000 | 5 | 49.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx049915-il | 500,000 | 9 | 113.5 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx049915-il | 500,000 | 5 | 114.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx049915-il | 1,000,000 | 9 | 155 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx049915-il | 1,000,000 | 5 | 152.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v23010-il | 50,000 | 9 | 23.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 50,000 | 5 | 27.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v23010-il | 100,000 | 9 | 35.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 100,000 | 5 | 41.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v23010-il | 200,000 | 9 | 54.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 200,000 | 5 | 57.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v23010-il | 500,000 | 9 | 79.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 500,000 | 5 | 78 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v23010-il | 1,000,000 | 9 | 97.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 1,000,000 | 5 | 94.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 50,000 | 9 | 23.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 50,000 | 5 | 27.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 9 | 36.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 5 | 39.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 9 | 51.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 5 | 53.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 9 | 74.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 5 | 76.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 9 | 98.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 5 | 95 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180sm-il | 50,000 | 9 | 3.9 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 50,000 | 5 | 6.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180sm-il | 100,000 | 9 | 4.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 100,000 | 5 | 23.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180sm-il | 200,000 | 9 | 27.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 200,000 | 5 | 55.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180sm-il | 500,000 | 9 | 102.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 500,000 | 5 | 106.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180sm-il | 1,000,000 | 9 | 146.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 1,000,000 | 5 | 145.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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