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 | ||
(e168-il) E168 (12.45%) | Eppler E168 low Reynolds number airfoil Max thickness 12.4% at 26.7% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(cootie-il) WACO COOTIE AIRFOIL | Waco Cootie airfoil Max thickness 8.5% at 30% chord Max camber 5.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(fx2-il) WORTMANN FX 2 AIRFOIL | Wortmann FX 2 airfoil Max thickness 20.4% at 43.5% chord Max camber 3.8% at 69.1% chord | Remove Airfoil details Airfoil plotter |
(ag24-il) AG24 Bubble Dancer DLG by Mark Drela | Drela AG24 airfoil used on the Bubble Dancer R/C DLG Max thickness 8.4% at 26% chord Max camber 2.2% at 46.9% chord | Remove Airfoil details Airfoil plotter |
(raf30-il) RAF 30 AIRFOIL | RAF-30 airfoil Max thickness 12.6% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(m24-il) NACA M24 AIRFOIL | NACA/Munk M-24 airfoil Max thickness 12% at 30.1% chord Max camber 6.3% at 30.1% chord | Remove Airfoil details Airfoil plotter |
(giiic-il) GIII BL75 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 9.9% at 39.8% chord Max camber 0.9% at 29.8% chord | Remove Airfoil details Airfoil plotter |
(a18sm-il) A18 (smoothed) | Archer A18 F1C free flight airfoil (smoothed) Max thickness 7.3% at 27.1% chord Max camber 3.8% at 49.3% chord | Remove Airfoil details Airfoil plotter |
(e211-il) E211 (10.96%) | Eppler E211 low Reynolds number airfoil Max thickness 10.9% at 31.7% chord Max camber 2.2% at 65.7% chord | Remove Airfoil details Airfoil plotter |
(e407-il) EPPLER 407 AIRFOIL | Eppler E407 sailplane airfoil Max thickness 14.4% at 36.6% chord Max camber 3.5% at 71.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e168-il,cootie-il,fx2-il,ag24-il,raf30-il,m24-il,giiic-il,a18sm-il,e211-il,e407-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e168-il | 50,000 | 9 | 22.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 50,000 | 5 | 28 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 100,000 | 9 | 38.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 100,000 | 5 | 40.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 200,000 | 9 | 53.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 200,000 | 5 | 52.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 500,000 | 9 | 73 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 500,000 | 5 | 67.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 1,000,000 | 9 | 87 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 1,000,000 | 5 | 77.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cootie-il | 50,000 | 9 | 36.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cootie-il | 50,000 | 5 | 39.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cootie-il | 100,000 | 9 | 60.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cootie-il | 100,000 | 5 | 62.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cootie-il | 200,000 | 9 | 84 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cootie-il | 200,000 | 5 | 83.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cootie-il | 500,000 | 9 | 116 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cootie-il | 500,000 | 5 | 107.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cootie-il | 1,000,000 | 9 | 136.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cootie-il | 1,000,000 | 5 | 121.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 50,000 | 9 | 18 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 50,000 | 5 | 14.9 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 100,000 | 9 | 23.7 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 100,000 | 5 | 22.7 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 200,000 | 9 | 34.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 200,000 | 5 | 34.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 500,000 | 9 | 51.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 500,000 | 5 | 50.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 1,000,000 | 9 | 107.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 1,000,000 | 5 | 111 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag24-il | 50,000 | 9 | 34.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag24-il | 50,000 | 5 | 38.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag24-il | 100,000 | 9 | 52.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag24-il | 100,000 | 5 | 52.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag24-il | 200,000 | 9 | 70.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag24-il | 200,000 | 5 | 66.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag24-il | 500,000 | 9 | 92.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag24-il | 500,000 | 5 | 83.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag24-il | 1,000,000 | 9 | 107.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag24-il | 1,000,000 | 5 | 96.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 50,000 | 9 | 28.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 50,000 | 5 | 28.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 100,000 | 9 | 41.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 100,000 | 5 | 39.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 200,000 | 9 | 52.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 200,000 | 5 | 45.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 500,000 | 9 | 58.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 500,000 | 5 | 58.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 1,000,000 | 9 | 69.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 1,000,000 | 5 | 71.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m24-il | 50,000 | 9 | 5.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m24-il | 50,000 | 5 | 19.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m24-il | 100,000 | 9 | 25.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m24-il | 100,000 | 5 | 45.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m24-il | 200,000 | 9 | 67.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m24-il | 200,000 | 5 | 71.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m24-il | 500,000 | 9 | 104.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m24-il | 500,000 | 5 | 100.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m24-il | 1,000,000 | 9 | 129.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m24-il | 1,000,000 | 5 | 118.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiic-il | 50,000 | 9 | 30.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiic-il | 50,000 | 5 | 31 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiic-il | 100,000 | 9 | 44.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiic-il | 100,000 | 5 | 42.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiic-il | 200,000 | 9 | 58.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiic-il | 200,000 | 5 | 51.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiic-il | 500,000 | 9 | 68.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiic-il | 500,000 | 5 | 60.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiic-il | 1,000,000 | 9 | 75.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiic-il | 1,000,000 | 5 | 71 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18sm-il | 50,000 | 9 | 44.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 50,000 | 5 | 44.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18sm-il | 100,000 | 9 | 65.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 100,000 | 5 | 63.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18sm-il | 200,000 | 9 | 87 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 200,000 | 5 | 81.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18sm-il | 500,000 | 9 | 114.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 500,000 | 5 | 102.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18sm-il | 1,000,000 | 9 | 132.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 1,000,000 | 5 | 116 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e211-il | 50,000 | 9 | 37.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e211-il | 50,000 | 5 | 39.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e211-il | 100,000 | 9 | 58.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e211-il | 100,000 | 5 | 57.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e211-il | 200,000 | 9 | 78.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e211-il | 200,000 | 5 | 74.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e211-il | 500,000 | 9 | 106.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e211-il | 500,000 | 5 | 91.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e211-il | 1,000,000 | 9 | 118.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e211-il | 1,000,000 | 5 | 100.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e407-il | 50,000 | 9 | 34.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e407-il | 50,000 | 5 | 30.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e407-il | 100,000 | 9 | 50.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e407-il | 100,000 | 5 | 48.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e407-il | 200,000 | 9 | 72 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e407-il | 200,000 | 5 | 72 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e407-il | 500,000 | 9 | 113 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e407-il | 500,000 | 5 | 104.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e407-il | 1,000,000 | 9 | 144.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e407-il | 1,000,000 | 5 | 121.5 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||