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 | ||
(waspsm-il) WASP (smoothed) | Mike Fox WASP low Reynolds number airfoil Max thickness 9.4% at 27.1% chord Max camber 3% at 37.9% chord | Remove Airfoil details Airfoil plotter |
(b737b-il) BOEING 737 MIDSPAN AIRFOIL | Boeing Commercial Airplane Company model 737 airfoils Max thickness 12.5% at 29.7% chord Max camber 0.8% at 10% chord | Remove Airfoil details Airfoil plotter |
(m20-il) NACA M20 AIRFOIL | NACA/Munk M-20 airfoil Max thickness 8.2% at 30% chord Max camber 6.1% at 30% chord | Remove Airfoil details Airfoil plotter |
(clarkk-il) CLARK K AIRFOIL | CLARK K airfoil Max thickness 11.7% at 29.7% chord Max camber 3.3% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(m1-il) NACA-M1 AIRFOIL | NACA/Munk M-1 airfoil Max thickness 6.2% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(c5e-il) LOCKHEED C-5A BL1256 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 10.8% at 40% chord Max camber 1.4% at 30% chord | Remove Airfoil details Airfoil plotter |
(ch10sm-il) CH10 (smoothed) | Chuch Hollinger CH 10-48-13 high lift low Reynolds number airfoil Max thickness 12.8% at 30.6% chord Max camber 10.2% at 49.3% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (waspsm-il,b737b-il,m20-il,clarkk-il,m1-il,c5e-il,ch10sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| waspsm-il | 50,000 | 9 | 31.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| waspsm-il | 50,000 | 5 | 37.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| waspsm-il | 100,000 | 9 | 51 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| waspsm-il | 100,000 | 5 | 53.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| waspsm-il | 200,000 | 9 | 69.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| waspsm-il | 200,000 | 5 | 69.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| waspsm-il | 500,000 | 9 | 96 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| waspsm-il | 500,000 | 5 | 91 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| waspsm-il | 1,000,000 | 9 | 115.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| waspsm-il | 1,000,000 | 5 | 108.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 50,000 | 9 | 23.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 50,000 | 5 | 26.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 100,000 | 9 | 34.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 100,000 | 5 | 37.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 200,000 | 9 | 47.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 200,000 | 5 | 51 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 500,000 | 9 | 69.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 500,000 | 5 | 71.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 1,000,000 | 9 | 88.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 1,000,000 | 5 | 87.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 50,000 | 9 | 10.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 50,000 | 5 | 26.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 100,000 | 9 | 55.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 100,000 | 5 | 56.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 200,000 | 9 | 78.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 200,000 | 5 | 78 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 500,000 | 9 | 108.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 500,000 | 5 | 105.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 1,000,000 | 9 | 131.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 1,000,000 | 5 | 125.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 50,000 | 9 | 32.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 50,000 | 5 | 36.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 100,000 | 9 | 54.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 100,000 | 5 | 54.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 200,000 | 9 | 75.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 200,000 | 5 | 71.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 500,000 | 9 | 102.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 500,000 | 5 | 91.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 1,000,000 | 9 | 121.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 1,000,000 | 5 | 104.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m1-il | 50,000 | 9 | 18.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 50,000 | 5 | 20.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m1-il | 100,000 | 9 | 27.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 100,000 | 5 | 24.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m1-il | 200,000 | 9 | 32.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 200,000 | 5 | 32.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m1-il | 500,000 | 9 | 38.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 500,000 | 5 | 50.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m1-il | 1,000,000 | 9 | 56 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 1,000,000 | 5 | 63.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 50,000 | 9 | 31.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 50,000 | 5 | 31.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 100,000 | 9 | 46.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 100,000 | 5 | 42.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 200,000 | 9 | 59.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 200,000 | 5 | 47.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 500,000 | 9 | 67.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 500,000 | 5 | 64.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 1,000,000 | 9 | 77.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 1,000,000 | 5 | 81 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 50,000 | 9 | 6.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 50,000 | 5 | 12.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 100,000 | 9 | 10.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 100,000 | 5 | 38.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 200,000 | 9 | 73.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 200,000 | 5 | 86.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 500,000 | 9 | 135.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 500,000 | 5 | 132.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 1,000,000 | 9 | 175.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 1,000,000 | 5 | 164 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||