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 |
(s102s-il) SOMERS S102 AIRFOIL (SHARP) | Dan Somers airfoil for the Toyota general aviation airplane Max thickness 15% at 40% chord Max camber 2.1% at 68.7% chord | Remove Airfoil details Airfoil plotter |
(s1014-il) S1014 | Selig S1014 HPV airfoil Max thickness 16.5% at 42.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (kc135d-il,s102s-il,s1014-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 | |
| s102s-il | 50,000 | 9 | 30.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 50,000 | 5 | 26.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102s-il | 100,000 | 9 | 40.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 100,000 | 5 | 42.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102s-il | 200,000 | 9 | 59.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 200,000 | 5 | 57 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102s-il | 500,000 | 9 | 82.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 500,000 | 5 | 69.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102s-il | 1,000,000 | 9 | 95.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 1,000,000 | 5 | 82.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1014-il | 50,000 | 9 | 27 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1014-il | 50,000 | 5 | 20.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1014-il | 100,000 | 9 | 38.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1014-il | 100,000 | 5 | 23.2 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1014-il | 200,000 | 9 | 33.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1014-il | 200,000 | 5 | 30.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1014-il | 500,000 | 9 | 45.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1014-il | 500,000 | 5 | 42 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1014-il | 1,000,000 | 9 | 54.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1014-il | 1,000,000 | 5 | 52.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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