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 | ||
(bacj-il) BOEING AIRFOIL J (no closed TE) | Boeing Commercial Airplane Company airfoil J Max thickness 10.1% at 40% chord Max camber 1.7% at 78% chord | Remove Airfoil details Airfoil plotter |
(ag08-il) AG08 | Drela AG08 airfoil Max thickness 5.8% at 21% chord Max camber 1.7% at 40.4% chord | Remove Airfoil details Airfoil plotter |
(ag19-il) AG19 | Drela AG19 airfoil Max thickness 5.4% at 20.6% chord Max camber 2.2% at 44.2% chord | Remove Airfoil details Airfoil plotter |
(l1003-il) LIEBECK L1003 AIRFOIL | Liebeck high lift airfoil Max thickness 17.7% at 30% chord Max camber 6.5% at 30% chord | Remove Airfoil details Airfoil plotter |
(s1046-il) S1046 17% (Danny Howell) | Selig S1046 airfoil Max thickness 17% at 30.8% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(m22-il) NACA M22 AIRFOIL | NACA/Munk M-22 airfoil Max thickness 6.3% at 30% chord Max camber 6.3% at 30% chord | Remove Airfoil details Airfoil plotter |
(m19-il) NACA M19 AIRFOIL | NACA/Munk M-19 airfoil Max thickness 6.2% at 30% chord Max camber 6% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (bacj-il,ag08-il,ag19-il,l1003-il,s1046-il,m22-il,m19-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| bacj-il | 50,000 | 9 | 20.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 50,000 | 5 | 20.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacj-il | 100,000 | 9 | 27 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 100,000 | 5 | 25 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacj-il | 200,000 | 9 | 31.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 200,000 | 5 | -1 at α=-100° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacj-il | 500,000 | 9 | 51.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 1,000,000 | 9 | 61.3 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 50,000 | 9 | 32.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 50,000 | 5 | 33.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 100,000 | 9 | 45.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 100,000 | 5 | 45.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 200,000 | 9 | 58.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 200,000 | 5 | 56.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 500,000 | 9 | 76.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 500,000 | 5 | 72 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 1,000,000 | 9 | 89 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 1,000,000 | 5 | 83.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 50,000 | 9 | 36.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 50,000 | 5 | 37.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 100,000 | 9 | 51.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 100,000 | 5 | 48.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 200,000 | 9 | 66.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 200,000 | 5 | 60.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 500,000 | 9 | 81.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 500,000 | 5 | 77.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 1,000,000 | 9 | 95.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 1,000,000 | 5 | 90.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 50,000 | 9 | 4.1 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 50,000 | 5 | 5.2 at α=17.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 100,000 | 9 | 4.5 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 100,000 | 5 | 7 at α=17.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 200,000 | 9 | 10.2 at α=18.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 200,000 | 5 | 10.1 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 500,000 | 9 | 74.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 500,000 | 5 | 68.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 1,000,000 | 9 | 104.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 1,000,000 | 5 | 68.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1046-il | 50,000 | 9 | 16.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1046-il | 50,000 | 5 | 25.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1046-il | 100,000 | 9 | 37.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1046-il | 100,000 | 5 | 40.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1046-il | 200,000 | 9 | 55 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1046-il | 200,000 | 5 | 54.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1046-il | 500,000 | 9 | 77 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1046-il | 500,000 | 5 | 70.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1046-il | 1,000,000 | 9 | 90.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1046-il | 1,000,000 | 5 | 80.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m22-il | 50,000 | 9 | 18.7 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m22-il | 50,000 | 5 | 32.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m22-il | 100,000 | 9 | 54.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m22-il | 100,000 | 5 | 55.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m22-il | 200,000 | 9 | 74.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m22-il | 200,000 | 5 | 73.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m22-il | 500,000 | 9 | 100.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m22-il | 500,000 | 5 | 81.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m22-il | 1,000,000 | 9 | 115 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m22-il | 1,000,000 | 5 | 91 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 50,000 | 9 | 20.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 50,000 | 5 | 37.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 100,000 | 9 | 57.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 100,000 | 5 | 57.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 200,000 | 9 | 77.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 200,000 | 5 | 75.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 500,000 | 9 | 102.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 500,000 | 5 | 83 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 1,000,000 | 9 | 117.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 1,000,000 | 5 | 92.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||