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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(ua79sff-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT | University of Alberta/Marsden UA 79-SF-187 sailplane airfoil FLAP Max thickness 8.7% at 73.1% chord Max camber 3.4% at 78.1% chord | Remove Airfoil details Airfoil plotter |
(vr11x-il) BOEING-VERTOL VR-11X AIRFOIL | Boeing-Vertol/NASA/Dadone VR-11X transonic rotorcraft airfoil Max thickness 11% at 40% chord Max camber 2.4% at 25% chord | Remove Airfoil details Airfoil plotter |
(ua2-180-il) UA(2)-180 (University of Alberta/Marsden) | UA(2)-180 airfoil for ultralight category aircraft Max thickness 18.1% at 31.5% chord Max camber 7% at 36.6% chord | Remove Airfoil details Airfoil plotter |
(uag8814320-il) UAG 88-143/20 | UAG 88-143/20 airfoil Max thickness 14.3% at 43.5% chord Max camber 6.2% at 46.7% chord | Remove Airfoil details Airfoil plotter |
(kc135a-il) KC-135 BL52.44 AIRFOIL | Boeing KC-135 transonic airfoils Max thickness 15.5% at 35% chord Max camber 1.3% at 20% chord | Remove Airfoil details Airfoil plotter |
(rae104-il) RAE 104 AIRFOIL | RAE 104 airfoil Max thickness 10% at 42% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ua79sff-il,vr11x-il,ua2-180-il,uag8814320-il,kc135a-il,rae104-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ua79sff-il | 50,000 | 9 | 3.4 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 50,000 | 5 | 3.5 at α=19.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 100,000 | 9 | 3.6 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 100,000 | 5 | 4.1 at α=18.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 200,000 | 9 | 3.8 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 200,000 | 5 | 5.1 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 500,000 | 9 | 6.4 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 500,000 | 5 | 25.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 1,000,000 | 9 | 60.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 1,000,000 | 5 | 62 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 50,000 | 9 | 30.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 50,000 | 5 | 29.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 100,000 | 9 | 41 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 100,000 | 5 | 39.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 200,000 | 9 | 55.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 200,000 | 5 | 51.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 500,000 | 9 | 71.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 500,000 | 5 | 73.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 1,000,000 | 9 | 92.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 1,000,000 | 5 | 89.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180-il | 50,000 | 9 | 3.9 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180-il | 50,000 | 5 | 6.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180-il | 100,000 | 9 | 5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180-il | 100,000 | 5 | 23.8 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180-il | 200,000 | 9 | 30.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180-il | 200,000 | 5 | 55.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180-il | 500,000 | 9 | 103.9 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180-il | 500,000 | 5 | 107 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180-il | 1,000,000 | 9 | 146.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180-il | 1,000,000 | 5 | 139.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| uag8814320-il | 50,000 | 9 | 5.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 50,000 | 5 | 15.3 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| uag8814320-il | 100,000 | 9 | 32 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 100,000 | 5 | 30.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| uag8814320-il | 200,000 | 9 | 55.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 200,000 | 5 | 53.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| uag8814320-il | 500,000 | 9 | 127 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 500,000 | 5 | 123.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| uag8814320-il | 1,000,000 | 9 | 185.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 1,000,000 | 5 | 169.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135a-il | 50,000 | 9 | 24.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 50,000 | 5 | 27.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135a-il | 100,000 | 9 | 47.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 100,000 | 5 | 47.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135a-il | 200,000 | 9 | 68.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 200,000 | 5 | 62.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135a-il | 500,000 | 9 | 88.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 500,000 | 5 | 73.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135a-il | 1,000,000 | 9 | 97.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 1,000,000 | 5 | 82.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae104-il | 50,000 | 9 | 24.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae104-il | 50,000 | 5 | 26.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae104-il | 100,000 | 9 | 39.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae104-il | 100,000 | 5 | 33.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae104-il | 200,000 | 9 | 44.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae104-il | 200,000 | 5 | 36.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae104-il | 500,000 | 9 | 52.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae104-il | 500,000 | 5 | 49.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae104-il | 1,000,000 | 9 | 58.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae104-il | 1,000,000 | 5 | 61.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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