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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(stcyr234-il) St. CYR 234 (Bartel 17-IC) | St. CYR 234 (Bartel 17-IC) airfoil Max thickness 16% at 20% chord Max camber 5.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(gu255118-il) UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL | University of Glasgow GU 25-5(11)8 canard airfoil (Quickie Max thickness 20% at 40% chord Max camber 7.1% at 45% chord | Remove Airfoil details Airfoil plotter |
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Polars for (stcyr234-il,gu255118-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| stcyr234-il | 50,000 | 9 | 28 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr234-il | 50,000 | 5 | 26.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr234-il | 100,000 | 9 | 47.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr234-il | 100,000 | 5 | 42.1 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr234-il | 200,000 | 9 | 72.9 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr234-il | 200,000 | 5 | 58 at α=0° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr234-il | 500,000 | 9 | 87.3 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr234-il | 500,000 | 5 | 66.5 at α=-1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr234-il | 1,000,000 | 9 | 93.7 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr234-il | 1,000,000 | 5 | 67.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gu255118-il | 50,000 | 9 | 3.9 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gu255118-il | 50,000 | 5 | 6.7 at α=17.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gu255118-il | 100,000 | 9 | 11.2 at α=18.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gu255118-il | 100,000 | 5 | 10.7 at α=17° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gu255118-il | 200,000 | 9 | 17.4 at α=16.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gu255118-il | 200,000 | 5 | 38.3 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gu255118-il | 500,000 | 9 | 63.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gu255118-il | 500,000 | 5 | 93.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gu255118-il | 1,000,000 | 9 | 136.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gu255118-il | 1,000,000 | 5 | 137.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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