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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(s4083-il) S4083 (8%) | Selig S4083 low Reynolds number airfoil Max thickness 8% at 22.5% chord Max camber 3.4% at 35.5% chord | Remove Airfoil details Airfoil plotter |
(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 |
(gs1-il) SIKORSKY GS-1 AIRFOIL | Gluharoff/Sikorsky GS-1 airfoil Max thickness 13.9% at 30% chord Max camber 4.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe499-il) GOE 499 AIRFOIL | Gottingen 499 airfoil Max thickness 6.8% at 30% chord Max camber 5.9% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s4083-il,kc135d-il,gs1-il,goe499-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s4083-il | 50,000 | 9 | 31.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 50,000 | 5 | 38.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 100,000 | 9 | 51.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 100,000 | 5 | 56.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 200,000 | 9 | 73.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 200,000 | 5 | 74.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 500,000 | 9 | 102.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 500,000 | 5 | 98.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 1,000,000 | 9 | 124.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 1,000,000 | 5 | 115.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| gs1-il | 50,000 | 9 | 9.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 50,000 | 5 | 29.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gs1-il | 100,000 | 9 | 51 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 100,000 | 5 | 54.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gs1-il | 200,000 | 9 | 74.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 200,000 | 5 | 74.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gs1-il | 500,000 | 9 | 105.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 500,000 | 5 | 100.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gs1-il | 1,000,000 | 9 | 129.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 1,000,000 | 5 | 119.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe499-il | 50,000 | 9 | 38.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 50,000 | 5 | 44.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe499-il | 100,000 | 9 | 71.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 100,000 | 5 | 69.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe499-il | 200,000 | 9 | 102.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 200,000 | 5 | 99.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe499-il | 500,000 | 9 | 149.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 500,000 | 5 | 118.3 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe499-il | 1,000,000 | 9 | 157.8 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 1,000,000 | 5 | 111.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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