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 |
(usnps4-il) USNPS4 (smoothed) | Jacobs USNPS4 (smoothed) 17.5 kW wind turbine airfoil Max thickness 11.9% at 34.2% chord Max camber 5% at 34.2% chord | Remove Airfoil details Airfoil plotter |
(goe796-il) GOE 796 AIRFOIL | Gottingen 796 airfoil Max thickness 12% at 30% chord Max camber 3.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe319-il) GOE 319 (HANSA-BRANDENBURG II) AIRFOIL | Gottingen 319 (Hansa-Brandenburg II) airfoil Max thickness 10.3% at 29.8% chord Max camber 5.8% at 29.8% chord | Remove Airfoil details Airfoil plotter |
(goe389-il) GOE 389 AIRFOIL | Gottingen 389 airfoil Max thickness 10.3% at 29.8% chord Max camber 4% at 39.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (kc135d-il,usnps4-il,goe796-il,goe319-il,goe389-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 | |
| usnps4-il | 50,000 | 9 | 32.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usnps4-il | 50,000 | 5 | 37.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usnps4-il | 100,000 | 9 | 55.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usnps4-il | 100,000 | 5 | 53.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usnps4-il | 200,000 | 9 | 74.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usnps4-il | 200,000 | 5 | 67.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usnps4-il | 500,000 | 9 | 95.2 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usnps4-il | 500,000 | 5 | 87.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usnps4-il | 1,000,000 | 9 | 110.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usnps4-il | 1,000,000 | 5 | 105.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 50,000 | 9 | 32.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 50,000 | 5 | 35.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 100,000 | 9 | 55.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 100,000 | 5 | 55.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 200,000 | 9 | 78 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 200,000 | 5 | 73.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 500,000 | 9 | 105.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 500,000 | 5 | 90.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 1,000,000 | 9 | 122.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 1,000,000 | 5 | 105.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe319-il | 50,000 | 9 | 26.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe319-il | 50,000 | 5 | 36.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe319-il | 100,000 | 9 | 53.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe319-il | 100,000 | 5 | 55.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe319-il | 200,000 | 9 | 75.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe319-il | 200,000 | 5 | 71.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe319-il | 500,000 | 9 | 101.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe319-il | 500,000 | 5 | 91.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe319-il | 1,000,000 | 9 | 114 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe319-il | 1,000,000 | 5 | 112.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe389-il | 50,000 | 9 | 32.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe389-il | 50,000 | 5 | 37.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe389-il | 100,000 | 9 | 55 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe389-il | 100,000 | 5 | 56.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe389-il | 200,000 | 9 | 75.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe389-il | 200,000 | 5 | 73.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe389-il | 500,000 | 9 | 101.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe389-il | 500,000 | 5 | 94.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe389-il | 1,000,000 | 9 | 119.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe389-il | 1,000,000 | 5 | 108.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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