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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(wb13535sm-il) WB-135/35 13.5% smoothed | Woody Blanchard WB135/35 R/C sailplane airfoil Max thickness 13.6% at 25% chord Max camber 3.8% at 50% chord | Remove Airfoil details Airfoil plotter |
(fx60100sm-il) FX60-100 10.0% smoothed | Wortmann FX 60-100 airfoil (smoothed) Max thickness 10% at 27.9% chord Max camber 3.5% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(ultimate-il) ULTIMATE | Carl Goldberg R/C Ultimate Bipe airfoil Max thickness 12.8% at 34.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(dh4009sm-il) dh4009sm | Dale House DH4009 (smoothed) used on the Storm R/C aerobatic aircraft Max thickness 8.9% at 41.6% chord Max camber 0.2% at 9.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (wb13535sm-il,fx60100sm-il,ultimate-il,dh4009sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| wb13535sm-il | 50,000 | 9 | 26.6 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| wb13535sm-il | 50,000 | 5 | 33.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| wb13535sm-il | 100,000 | 9 | 51.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| wb13535sm-il | 100,000 | 5 | 51.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| wb13535sm-il | 200,000 | 9 | 73.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| wb13535sm-il | 200,000 | 5 | 68.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| wb13535sm-il | 500,000 | 9 | 101.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| wb13535sm-il | 500,000 | 5 | 84.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| wb13535sm-il | 1,000,000 | 9 | 108.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| wb13535sm-il | 1,000,000 | 5 | 102.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 50,000 | 9 | 40.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 50,000 | 5 | 42.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 100,000 | 9 | 62.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 100,000 | 5 | 61.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 200,000 | 9 | 85.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 200,000 | 5 | 79.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 500,000 | 9 | 112.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 500,000 | 5 | 91.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 1,000,000 | 9 | 120.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 1,000,000 | 5 | 100.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 50,000 | 9 | 28.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 50,000 | 5 | 27.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 100,000 | 9 | 39 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 100,000 | 5 | 36.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 200,000 | 9 | 47.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 200,000 | 5 | 42 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 500,000 | 9 | 55.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 500,000 | 5 | 53.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 1,000,000 | 9 | 63.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 1,000,000 | 5 | 67 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dh4009sm-il | 50,000 | 9 | 19.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dh4009sm-il | 50,000 | 5 | 24.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dh4009sm-il | 100,000 | 9 | 27.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dh4009sm-il | 100,000 | 5 | 31.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dh4009sm-il | 200,000 | 9 | 40.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dh4009sm-il | 200,000 | 5 | 34.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dh4009sm-il | 500,000 | 9 | 48.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dh4009sm-il | 500,000 | 5 | 42.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dh4009sm-il | 1,000,000 | 9 | 51.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dh4009sm-il | 1,000,000 | 5 | 53.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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