Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(kc135d-il) KC-135 BL351.6 AIRFOIL | Boeing KC-135 transonic airfoils Max thickness 9% at 40% chord Max camber 1.9% at 30% chord | Remove Airfoil details Airfoil plotter |
(mh24-il) MH 24 9.01% | Martin Hepperle MH 24 for F3D Pylon Racing (extended laminar flow) Max thickness 9% at 37.3% chord Max camber 1.2% at 37.3% chord | Remove Airfoil details Airfoil plotter |
(kc135winglet-il) KC-135 Winglet (supercritical Whitcomb) | Boeing KC-135 winglet airfoil designed by Richard T. Whitcomb Max thickness 8% at 40% chord Max camber 2.7% at 65% 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 |
(m27-il) NACA M27 AIRFOIL | NACA/Munk M-27 airfoil Max thickness 12% at 30.1% chord Max camber 8.4% at 30.1% chord | Remove Airfoil details Airfoil plotter |
(m10-il) NACA M10 AIRFOIL | NACA/Munk M-10 airfoil Max thickness 6.2% at 30% chord Max camber 1.9% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (kc135d-il,mh24-il,kc135winglet-il,m21-il,m27-il,m10-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| kc135d-il | 50,000 | 9 | 36.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 50,000 | 5 | 36.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 100,000 | 9 | 54.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 100,000 | 5 | 52.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 200,000 | 9 | 74.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 200,000 | 5 | 68.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 500,000 | 9 | 100.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 500,000 | 5 | 84 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 1,000,000 | 9 | 114.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 1,000,000 | 5 | 86.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 50,000 | 9 | 34.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 50,000 | 5 | 33 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 100,000 | 9 | 50.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 100,000 | 5 | 47 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 200,000 | 9 | 68.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 200,000 | 5 | 59.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 500,000 | 9 | 79.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 500,000 | 5 | 61.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 1,000,000 | 9 | 74.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 1,000,000 | 5 | 70.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135winglet-il | 50,000 | 9 | 40.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 50,000 | 5 | 40.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135winglet-il | 100,000 | 9 | 62.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 100,000 | 5 | 59.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135winglet-il | 200,000 | 9 | 85.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 200,000 | 5 | 73.2 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135winglet-il | 500,000 | 9 | 103.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 500,000 | 5 | 88.7 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135winglet-il | 1,000,000 | 9 | 116.5 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 1,000,000 | 5 | 89.1 at α=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 | |
| m27-il | 50,000 | 9 | 4.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m27-il | 50,000 | 5 | 9.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m27-il | 100,000 | 9 | 9 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m27-il | 100,000 | 5 | 41.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m27-il | 200,000 | 9 | 62.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m27-il | 200,000 | 5 | 70.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m27-il | 500,000 | 9 | 105.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m27-il | 500,000 | 5 | 105 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m27-il | 1,000,000 | 9 | 135.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m27-il | 1,000,000 | 5 | 126.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m10-il | 50,000 | 9 | 34.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 50,000 | 5 | 34.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m10-il | 100,000 | 9 | 46.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 100,000 | 5 | 45.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m10-il | 200,000 | 9 | 58.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 200,000 | 5 | 54.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m10-il | 500,000 | 9 | 72.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 500,000 | 5 | 64.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m10-il | 1,000,000 | 9 | 80.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 1,000,000 | 5 | 75.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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