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 | ||
(mh121-il) MH 121 8.76% | Martin Hepperle MH 121 for tip section of a propeller Max thickness 8.8% at 37.9% chord Max camber 3% at 62.2% chord | Remove Airfoil details Airfoil plotter |
(fx711520-il) FX 71-L-150/20 AIRFOIL | Wortmann FX 71-L-150/20 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(fx711530-il) FX 71-L-150/30 AIRFOIL | Wortmann FX 71-L-150/30 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(fx711525-il) FX 71-L-150/25 AIRFOIL | Wortmann FX 71-L-150/25 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(du861372-il) DU 86-137/25 AIRFOIL | Delft University DU 86-137/25 Airfoil Max thickness 13.6% at 41.6% chord Max camber 0.3% at 1.6% chord | Remove Airfoil details Airfoil plotter |
(hq109-il) HQ 1.0/9 AIRFOIL | Quabeck HQ 1.0/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 1% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq309-il) HQ 3.0/9 AIRFOIL | Quabeck HQ 3.0/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (mh121-il,fx711520-il,fx711530-il,fx711525-il,du861372-il,hq109-il,hq309-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh121-il | 50,000 | 9 | 31.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 50,000 | 5 | 35.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 100,000 | 9 | 53.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 100,000 | 5 | 57.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 200,000 | 9 | 84 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 200,000 | 5 | 82.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 500,000 | 9 | 125.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 500,000 | 5 | 107.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 1,000,000 | 9 | 139.1 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 1,000,000 | 5 | 117.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711520-il | 50,000 | 9 | 27.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711520-il | 50,000 | 5 | 25.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711520-il | 100,000 | 9 | 36.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711520-il | 100,000 | 5 | 33.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711520-il | 200,000 | 9 | 44.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711520-il | 200,000 | 5 | 38.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711520-il | 500,000 | 9 | 49.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711520-il | 500,000 | 5 | 48 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711520-il | 1,000,000 | 9 | 57.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711520-il | 1,000,000 | 5 | 56.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711530-il | 50,000 | 9 | 27.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711530-il | 50,000 | 5 | 26.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711530-il | 100,000 | 9 | 39.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711530-il | 100,000 | 5 | 35.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711530-il | 200,000 | 9 | 47.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711530-il | 200,000 | 5 | 40.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711530-il | 500,000 | 9 | 51.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711530-il | 500,000 | 5 | 49.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711530-il | 1,000,000 | 9 | 59.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711530-il | 1,000,000 | 5 | 58.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711525-il | 50,000 | 9 | 27.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711525-il | 50,000 | 5 | 26.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711525-il | 100,000 | 9 | 38.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711525-il | 100,000 | 5 | 34.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711525-il | 200,000 | 9 | 46.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711525-il | 200,000 | 5 | 39.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711525-il | 500,000 | 9 | 50.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711525-il | 500,000 | 5 | 48.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711525-il | 1,000,000 | 9 | 58.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711525-il | 1,000,000 | 5 | 57.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du861372-il | 50,000 | 9 | 28.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 50,000 | 5 | 23.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du861372-il | 100,000 | 9 | 33.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 100,000 | 5 | 27.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du861372-il | 200,000 | 9 | 32.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 200,000 | 5 | 35.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du861372-il | 500,000 | 9 | 46.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 500,000 | 5 | 48.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du861372-il | 1,000,000 | 9 | 58.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 1,000,000 | 5 | 59.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq109-il | 50,000 | 9 | 32.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq109-il | 50,000 | 5 | 33.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq109-il | 100,000 | 9 | 48 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq109-il | 100,000 | 5 | 45 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq109-il | 200,000 | 9 | 62.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq109-il | 200,000 | 5 | 55.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq109-il | 500,000 | 9 | 79.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq109-il | 500,000 | 5 | 66.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq109-il | 1,000,000 | 9 | 82.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq109-il | 1,000,000 | 5 | 75.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq309-il | 50,000 | 9 | 39.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 50,000 | 5 | 41.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq309-il | 100,000 | 9 | 61.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 100,000 | 5 | 59.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq309-il | 200,000 | 9 | 84.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 200,000 | 5 | 78.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq309-il | 500,000 | 9 | 114.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 500,000 | 5 | 96.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq309-il | 1,000,000 | 9 | 132.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 1,000,000 | 5 | 101.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||