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 | ||
(naca0010-il) NACA 0010 | NACA 0010 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(stf86361-il) EPPLER STF 863-615 AIRFOIL | Eppler STF 863-615 airfoil Max thickness 14.7% at 44.7% chord Max camber 4.2% at 72.3% chord | Remove Airfoil details Airfoil plotter |
(clarym15-il) CLARK YM-15 AIRFOIL | CLARK YM15 airfoil Max thickness 15% at 29.6% chord Max camber 3.6% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(n63215b-il) NACA 63(2)-215 MOD B | NACA-NASA/AMES/Hicks 63(2)-215 MOD B airfoil Max thickness 15% at 30% chord Max camber 1.5% at 10% chord | Remove Airfoil details Airfoil plotter |
(n64008a-il) NACA 64-008A AIRFOIL | NACA 64-008A airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (naca0010-il,stf86361-il,clarym15-il,n63215b-il,n64008a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca0010-il | 50,000 | 9 | 25.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0010-il | 50,000 | 5 | 25.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0010-il | 100,000 | 9 | 35.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0010-il | 100,000 | 5 | 33.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0010-il | 200,000 | 9 | 44.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0010-il | 200,000 | 5 | 42.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0010-il | 500,000 | 9 | 55.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0010-il | 500,000 | 5 | 57.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0010-il | 1,000,000 | 9 | 70.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0010-il | 1,000,000 | 5 | 74.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stf86361-il | 50,000 | 9 | 22.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stf86361-il | 50,000 | 5 | 23.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stf86361-il | 100,000 | 9 | 32.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stf86361-il | 100,000 | 5 | 34.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stf86361-il | 200,000 | 9 | 54.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stf86361-il | 200,000 | 5 | 56.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stf86361-il | 500,000 | 9 | 92.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stf86361-il | 500,000 | 5 | 98.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stf86361-il | 1,000,000 | 9 | 145.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stf86361-il | 1,000,000 | 5 | 142.7 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 50,000 | 9 | 12.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 50,000 | 5 | 31 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 100,000 | 9 | 47.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 100,000 | 5 | 48.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 200,000 | 9 | 66.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 200,000 | 5 | 62.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 500,000 | 9 | 88.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 500,000 | 5 | 84.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 1,000,000 | 9 | 109.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 1,000,000 | 5 | 105.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 50,000 | 9 | 25.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 50,000 | 5 | 24.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 100,000 | 9 | 32.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 100,000 | 5 | 35.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 200,000 | 9 | 44.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 200,000 | 5 | 47.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 500,000 | 9 | 66.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 500,000 | 5 | 68.3 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 1,000,000 | 9 | 86.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 1,000,000 | 5 | 83.9 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 50,000 | 9 | 19.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 50,000 | 5 | 23.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 100,000 | 9 | 32.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 100,000 | 5 | 30.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 200,000 | 9 | 41 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 200,000 | 5 | 35 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 500,000 | 9 | 46.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 500,000 | 5 | 44.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 1,000,000 | 9 | 49.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 1,000,000 | 5 | 59.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||