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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(giiig-il) GIII BL167 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 44.9% chord Max camber 1.3% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(geminism-il) GEMINI (smoothed) | GEMINI R/C sailplane airfoil (smoothed) Max thickness 15.4% at 34.2% chord Max camber 2.2% at 37.9% chord | Remove Airfoil details Airfoil plotter |
(kc135c-il) KC-135 BL200.76 AIRFOIL | Boeing KC-135 transonic airfoils Max thickness 10.6% at 40% chord Max camber 1.5% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (giiig-il,geminism-il,kc135c-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiig-il | 50,000 | 9 | 31.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 50,000 | 5 | 32.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiig-il | 100,000 | 9 | 46.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 100,000 | 5 | 44.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiig-il | 200,000 | 9 | 65.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 200,000 | 5 | 56.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiig-il | 500,000 | 9 | 78.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 500,000 | 5 | 62.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiig-il | 1,000,000 | 9 | 83 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 1,000,000 | 5 | 73 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| geminism-il | 50,000 | 9 | 8.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 50,000 | 5 | 28.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| geminism-il | 100,000 | 9 | 47.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 100,000 | 5 | 48.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| geminism-il | 200,000 | 9 | 66.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 200,000 | 5 | 65.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| geminism-il | 500,000 | 9 | 92.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 500,000 | 5 | 86.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| geminism-il | 1,000,000 | 9 | 110.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| geminism-il | 1,000,000 | 5 | 100.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135c-il | 50,000 | 9 | 34.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 50,000 | 5 | 34.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135c-il | 100,000 | 9 | 52 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 100,000 | 5 | 50.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135c-il | 200,000 | 9 | 71.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 200,000 | 5 | 66 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135c-il | 500,000 | 9 | 91.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 500,000 | 5 | 73.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135c-il | 1,000,000 | 9 | 100.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 1,000,000 | 5 | 78.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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