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 | ||
(m16-il) NACA M16 AIRFOIL | NACA/Munk M-16 airfoil Max thickness 6.2% at 30% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
(a18-il) A18 (original) | Archer A18 F1C free flight airfoil(original) Max thickness 7.3% at 30% chord Max camber 3.9% at 45% chord | Remove Airfoil details Airfoil plotter |
(c5c-il) LOCKHEED C-5A BL576 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord Max camber 1.4% at 65% chord | Remove Airfoil details Airfoil plotter |
(m17-il) NACA M17 AIRFOIL | NACA/Munk M-17 airfoil Max thickness 8.1% at 40% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
(m13-il) NACA M13 AIRFOIL | NACA/Munk M-13 airfoil Max thickness 6.2% at 30% chord Max camber 3.8% at 30% chord | Remove Airfoil details Airfoil plotter |
(m11-il) NACA M11 AIRFOIL | NACA/Munk M-11 airfoil Max thickness 8.2% at 30% chord Max camber 1.9% at 30% chord | Remove Airfoil details Airfoil plotter |
(m18-il) NACA M18 AIRFOIL | NACA/Munk M-18 airfoil Max thickness 12% at 30% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
(m15-il) NACA M15 AIRFOIL | NACA/Munk M-15 airfoil Max thickness 12% at 30% chord Max camber 3.8% at 30% chord | Remove Airfoil details Airfoil plotter |
(m25-il) NACA M25 AIRFOIL | NACA/Munk M-25 airfoil Max thickness 6.3% at 30% chord Max camber 8.2% at 30% chord | Remove Airfoil details Airfoil plotter |
(m21-il) NACA M21 AIRFOIL | NACA/Munk M-21 airfoil Max thickness 12% at 30% chord Max camber 6% at 30% chord | Remove Airfoil details Airfoil plotter |
(m23-il) NACA M23 AIRFOIL | NACA/Munk M-23 airfoil Max thickness 8.1% at 30.1% chord Max camber 6.4% at 30.1% chord | Remove Airfoil details Airfoil plotter |
(c5b-il) LOCKHEED C-5A BL488.2 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.5% at 40% chord Max camber 1.2% at 70% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (m16-il,a18-il,c5c-il,m17-il,m13-il,m11-il,m18-il,m15-il,m25-il,m21-il,m23-il,c5b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m16-il | 50,000 | 9 | 39 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 50,000 | 5 | 38.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 100,000 | 9 | 53.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 100,000 | 5 | 53.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 200,000 | 9 | 70.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 200,000 | 5 | 68.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 500,000 | 9 | 92.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 500,000 | 5 | 88.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 1,000,000 | 9 | 109.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 1,000,000 | 5 | 102.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18-il | 50,000 | 9 | 44 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 50,000 | 5 | 44.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18-il | 100,000 | 9 | 65 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 100,000 | 5 | 63.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18-il | 200,000 | 9 | 86.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 200,000 | 5 | 80.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18-il | 500,000 | 9 | 111.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 500,000 | 5 | 99.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18-il | 1,000,000 | 9 | 124.7 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 1,000,000 | 5 | 109.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 50,000 | 9 | 31.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 50,000 | 5 | 30.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 100,000 | 9 | 48.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 100,000 | 5 | 44.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 200,000 | 9 | 67.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 200,000 | 5 | 55.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 500,000 | 9 | 78.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 500,000 | 5 | 62.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 1,000,000 | 9 | 82.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 1,000,000 | 5 | 77.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 50,000 | 9 | 35.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 50,000 | 5 | 35.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 100,000 | 9 | 55.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 100,000 | 5 | 55.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 200,000 | 9 | 75.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 200,000 | 5 | 74.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 500,000 | 9 | 102.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 500,000 | 5 | 98.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 1,000,000 | 9 | 122.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 1,000,000 | 5 | 114.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m13-il | 50,000 | 9 | 38.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 50,000 | 5 | 40.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m13-il | 100,000 | 9 | 56.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 100,000 | 5 | 56.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m13-il | 200,000 | 9 | 74.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 200,000 | 5 | 73.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m13-il | 500,000 | 9 | 98.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 500,000 | 5 | 95 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m13-il | 1,000,000 | 9 | 115.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 1,000,000 | 5 | 86.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m11-il | 50,000 | 9 | 34.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 50,000 | 5 | 35.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m11-il | 100,000 | 9 | 50.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 100,000 | 5 | 48.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m11-il | 200,000 | 9 | 65.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 200,000 | 5 | 60.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m11-il | 500,000 | 9 | 84.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 500,000 | 5 | 75.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m11-il | 1,000,000 | 9 | 96.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 1,000,000 | 5 | 82.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m18-il | 50,000 | 9 | 11.1 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m18-il | 50,000 | 5 | 25.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m18-il | 100,000 | 9 | 47.3 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m18-il | 100,000 | 5 | 50.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m18-il | 200,000 | 9 | 71.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m18-il | 200,000 | 5 | 72.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m18-il | 500,000 | 9 | 103.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m18-il | 500,000 | 5 | 100.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m18-il | 1,000,000 | 9 | 127.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m18-il | 1,000,000 | 5 | 116.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 50,000 | 9 | 23.8 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 50,000 | 5 | 30 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 100,000 | 9 | 50.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 100,000 | 5 | 53.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 200,000 | 9 | 72.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 200,000 | 5 | 72.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 500,000 | 9 | 101.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 500,000 | 5 | 98.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 1,000,000 | 9 | 124.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 1,000,000 | 5 | 118.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 50,000 | 9 | 6.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 50,000 | 5 | 20.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 100,000 | 9 | 53.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 100,000 | 5 | 54.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 200,000 | 9 | 78.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 200,000 | 5 | 78.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 500,000 | 9 | 102.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 500,000 | 5 | 94.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 1,000,000 | 9 | 111.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 1,000,000 | 5 | 107.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m21-il | 50,000 | 9 | 5.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 50,000 | 5 | 22.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m21-il | 100,000 | 9 | 29.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 100,000 | 5 | 48.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m21-il | 200,000 | 9 | 70.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 200,000 | 5 | 73.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m21-il | 500,000 | 9 | 107.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 500,000 | 5 | 105.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m21-il | 1,000,000 | 9 | 135.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 1,000,000 | 5 | 128.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m23-il | 50,000 | 9 | 6.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m23-il | 50,000 | 5 | 23.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m23-il | 100,000 | 9 | 44.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m23-il | 100,000 | 5 | 53.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m23-il | 200,000 | 9 | 76.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m23-il | 200,000 | 5 | 76 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m23-il | 500,000 | 9 | 106.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m23-il | 500,000 | 5 | 102.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m23-il | 1,000,000 | 9 | 128.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m23-il | 1,000,000 | 5 | 117.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5b-il | 50,000 | 9 | 30.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 50,000 | 5 | 29.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5b-il | 100,000 | 9 | 46.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 100,000 | 5 | 42.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5b-il | 200,000 | 9 | 64.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 200,000 | 5 | 50.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5b-il | 500,000 | 9 | 73.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 500,000 | 5 | 61.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5b-il | 1,000,000 | 9 | 78.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 1,000,000 | 5 | 77.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||