Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(fx73cl2152-il) FX 73-CL2-152 | Wortmann FX 73-CL2-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 6.6% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(s1221-flap-il) S1221 w/ 4 deg flap | Selig S1221 airfoil with 4 deg flap Max thickness 12.1% at 21.8% chord Max camber 5.3% at 52.9% chord | Remove Airfoil details Airfoil plotter |
(fx74cl6140-il) FX 74-CL6-140 | Wortmann FX 74-CL6-140 airfoil Max thickness 14.1% at 30.9% chord Max camber 7.1% at 33.9% chord | Remove Airfoil details Airfoil plotter |
(fx73cl3152-il) FX 73-CL3-152 | Wortmann FX 73-CL3-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 8% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(fx74130wp2-il) 74-130 WP2 | Wortmann 74-130 WP2 airfoil Max thickness 13% at 43.5% chord Max camber 3.9% at 46.7% chord | Remove Airfoil details Airfoil plotter |
(fx74cl5140-il) FX74_CL5_140 | Wortmann FX 74-CL5-140 high lift airfoil Max thickness 14% at 30.9% chord Max camber 9.9% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(fx73cl1152-il) FX 73-CL1-152 | Wortmann FX 73-CL1-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 6.1% at 33.9% chord | Remove Airfoil details Airfoil plotter |
(fx74modsm-il) FX 74-Cl5-140 MOD (smoothed) | Modified Wortmann FX 74-CL5-140 high lift airfoil Max thickness 13.1% at 27.1% chord Max camber 9.7% at 41.6% chord | Remove Airfoil details Airfoil plotter |
(trainer60-il) TRAINER60 | Great Planes R/C Trainer 60 airfoil Max thickness 18.3% at 27.1% chord Max camber 0.1% at 1.3% chord | Remove Airfoil details Airfoil plotter |
(fx79w151a-il) FX 79-W-151 A | Wortmann FX 79-W-151 airfoil for use on wind turbines (W) A Max thickness 15.2% at 33.9% chord Max camber 3.8% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(fx79w660a-il) FX 79-W-660A | Wortman FX 79-W-660A airfoil for use on wind turbines (W) Max thickness 66.4% at 46.7% chord Max camber 2.3% at 17% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx73cl2152-il,s1221-flap-il,fx74cl6140-il,fx73cl3152-il,fx74130wp2-il,fx74cl5140-il,fx73cl1152-il,fx74modsm-il,trainer60-il,fx79w151a-il,fx79w660a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx73cl2152-il | 50,000 | 9 | 16.3 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 50,000 | 5 | 32.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 100,000 | 9 | 41.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 100,000 | 5 | 52.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 200,000 | 9 | 66.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 200,000 | 5 | 74.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 500,000 | 9 | 104.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 500,000 | 5 | 107.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 1,000,000 | 9 | 136.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 1,000,000 | 5 | 135.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 50,000 | 9 | 31 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 50,000 | 5 | 39.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 100,000 | 9 | 48.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 100,000 | 5 | 56.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 200,000 | 9 | 69.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 200,000 | 5 | 76.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 500,000 | 9 | 104.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 500,000 | 5 | 106.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 1,000,000 | 9 | 133.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 1,000,000 | 5 | 129.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 50,000 | 9 | 5.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 50,000 | 5 | 18.9 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 100,000 | 9 | 19.9 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 100,000 | 5 | 40.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 200,000 | 9 | 48.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 200,000 | 5 | 72 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 500,000 | 9 | 114.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 500,000 | 5 | 120.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 1,000,000 | 9 | 157.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 1,000,000 | 5 | 158.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl3152-il | 50,000 | 9 | 5.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 50,000 | 5 | 28.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl3152-il | 100,000 | 9 | 38.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 100,000 | 5 | 50.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl3152-il | 200,000 | 9 | 64 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 200,000 | 5 | 71 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl3152-il | 500,000 | 9 | 99.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 500,000 | 5 | 100.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl3152-il | 1,000,000 | 9 | 129.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 1,000,000 | 5 | 128.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp2-il | 50,000 | 9 | 23.1 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp2-il | 50,000 | 5 | 22.1 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp2-il | 100,000 | 9 | 37 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp2-il | 100,000 | 5 | 36.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp2-il | 200,000 | 9 | 72.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp2-il | 200,000 | 5 | 75.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp2-il | 500,000 | 9 | 125.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp2-il | 500,000 | 5 | 119.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp2-il | 1,000,000 | 9 | 161.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp2-il | 1,000,000 | 5 | 150.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 50,000 | 9 | 6.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 50,000 | 5 | 18.3 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 100,000 | 9 | 33.1 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 100,000 | 5 | 46.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 200,000 | 9 | 72.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 200,000 | 5 | 73.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 500,000 | 9 | 118.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 500,000 | 5 | 115.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 1,000,000 | 9 | 156.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 1,000,000 | 5 | 149.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 50,000 | 9 | 4.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 50,000 | 5 | 20.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 100,000 | 9 | 24.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 100,000 | 5 | 42.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 200,000 | 9 | 53.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 200,000 | 5 | 68.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 500,000 | 9 | 100.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 500,000 | 5 | 106.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 1,000,000 | 9 | 137.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 1,000,000 | 5 | 136.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74modsm-il | 50,000 | 9 | 6.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 50,000 | 5 | 28.8 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74modsm-il | 100,000 | 9 | 41.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 100,000 | 5 | 58.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74modsm-il | 200,000 | 9 | 76.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 200,000 | 5 | 84.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74modsm-il | 500,000 | 9 | 118.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 500,000 | 5 | 119.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74modsm-il | 1,000,000 | 9 | 152.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 1,000,000 | 5 | 149.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| trainer60-il | 50,000 | 9 | 15.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 50,000 | 5 | 24.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| trainer60-il | 100,000 | 9 | 36.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 100,000 | 5 | 38.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| trainer60-il | 200,000 | 9 | 51.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 200,000 | 5 | 50.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| trainer60-il | 500,000 | 9 | 73.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 500,000 | 5 | 65.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| trainer60-il | 1,000,000 | 9 | 85.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 1,000,000 | 5 | 79.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w151a-il | 50,000 | 9 | 4.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w151a-il | 50,000 | 5 | 19.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w151a-il | 100,000 | 9 | 35.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w151a-il | 100,000 | 5 | 47 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w151a-il | 200,000 | 9 | 69.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w151a-il | 200,000 | 5 | 71.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w151a-il | 500,000 | 9 | 104.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w151a-il | 500,000 | 5 | 102 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w151a-il | 1,000,000 | 9 | 132.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w151a-il | 1,000,000 | 5 | 126.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 50,000 | 9 | 0.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 50,000 | 5 | 3 at α=-10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 100,000 | 9 | 5.2 at α=-10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 100,000 | 5 | 5.5 at α=-5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 200,000 | 9 | 8.7 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 200,000 | 5 | 6 at α=-2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 500,000 | 9 | 5 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 500,000 | 5 | 4.7 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 1,000,000 | 9 | 6.5 at α=16.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 1,000,000 | 5 | 5.4 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||