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 | ||
(b707e-il) BOEING 707 .99 SPAN AIRFOIL | Boeing Commercial Airplane Company model 707 airfoils Max thickness 9% at 42% chord Max camber 1.8% at 34% chord | Remove Airfoil details Airfoil plotter |
(ag14-il) AG14 | Drela AG14 airfoil Max thickness 5.4% at 19.9% chord Max camber 2% at 41.9% chord | Remove Airfoil details Airfoil plotter |
(b29root-il) B-29 ROOT AIRFOIL | Boeing B-29 root airfoil Max thickness 22% at 30.2% chord Max camber 1.7% at 30.2% chord | Remove Airfoil details Airfoil plotter |
(s1221-il) S1221 w/o flap | Selig S1221 airfoil Max thickness 12.1% at 21.8% chord Max camber 4.9% at 49.1% chord | Remove Airfoil details Airfoil plotter |
(n5h10-il) NACA 5-H-10 AIRFOIL | NACA 5-H-10 rotorcraft airfoil Max thickness 9.9% at 40% chord Max camber 2.3% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (b707e-il,ag14-il,b29root-il,s1221-il,n5h10-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| b707e-il | 50,000 | 9 | 37 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 50,000 | 5 | 35.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707e-il | 100,000 | 9 | 53.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 100,000 | 5 | 48.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707e-il | 200,000 | 9 | 67.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 200,000 | 5 | 53.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707e-il | 500,000 | 9 | 65.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 500,000 | 5 | 64.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707e-il | 1,000,000 | 9 | 77.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 1,000,000 | 5 | 75.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag14-il | 50,000 | 9 | 34.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 50,000 | 5 | 35.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag14-il | 100,000 | 9 | 48.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 100,000 | 5 | 47.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag14-il | 200,000 | 9 | 62.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 200,000 | 5 | 59.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag14-il | 500,000 | 9 | 80.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 500,000 | 5 | 76 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag14-il | 1,000,000 | 9 | 93.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 1,000,000 | 5 | 89.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29root-il | 50,000 | 9 | 2.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29root-il | 50,000 | 5 | 8.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29root-il | 100,000 | 9 | 13.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29root-il | 100,000 | 5 | 34.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29root-il | 200,000 | 9 | 58.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29root-il | 200,000 | 5 | 52.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29root-il | 500,000 | 9 | 77.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29root-il | 500,000 | 5 | 68.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29root-il | 1,000,000 | 9 | 90.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29root-il | 1,000,000 | 5 | 83.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 50,000 | 9 | 27.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 50,000 | 5 | 36.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 100,000 | 9 | 45.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 100,000 | 5 | 54.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 200,000 | 9 | 70 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 200,000 | 5 | 76.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 500,000 | 9 | 107.5 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 500,000 | 5 | 110 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 1,000,000 | 9 | 137.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 1,000,000 | 5 | 135.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h10-il | 50,000 | 9 | 30.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h10-il | 50,000 | 5 | 31.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h10-il | 100,000 | 9 | 48.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h10-il | 100,000 | 5 | 48.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h10-il | 200,000 | 9 | 65.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h10-il | 200,000 | 5 | 56.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h10-il | 500,000 | 9 | 70 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h10-il | 500,000 | 5 | 58.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h10-il | 1,000,000 | 9 | 74.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h10-il | 1,000,000 | 5 | 69 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||