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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(cap21c-il) CAP 21 (TraCFoil) | CAP 21 (TraCFoil) airfoil Max thickness 15.6% at 15.7% chord Max camber 0.6% at 23.9% chord | Remove Airfoil details Airfoil plotter |
(e836-il) EPPLER E836 HYDROFOIL AIRFOIL | Eppler E836 hydrofoil Max thickness 12.6% at 42.8% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(ht12-il) HT12 | Drela HT12 airfoil Max thickness 5% at 18.6% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe367-il) GOE 367 AIRFOIL | Gottingen 367 airfoil Max thickness 16.3% at 29.7% chord Max camber 4.6% at 39.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (cap21c-il,e836-il,ht12-il,goe367-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cap21c-il | 50,000 | 9 | 9.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 50,000 | 5 | 14.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cap21c-il | 100,000 | 9 | 17.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 100,000 | 5 | 26 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cap21c-il | 200,000 | 9 | 38.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 200,000 | 5 | 48.1 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cap21c-il | 500,000 | 9 | 74 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 500,000 | 5 | 77.6 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cap21c-il | 1,000,000 | 9 | 97.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 1,000,000 | 5 | 97.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e836-il | 50,000 | 9 | 28.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e836-il | 50,000 | 5 | 28.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e836-il | 100,000 | 9 | 43.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e836-il | 100,000 | 5 | 34.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e836-il | 200,000 | 9 | 45.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e836-il | 200,000 | 5 | 42.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e836-il | 500,000 | 9 | 60 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e836-il | 500,000 | 5 | 49.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e836-il | 1,000,000 | 9 | 67.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e836-il | 1,000,000 | 5 | 59.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht12-il | 50,000 | 9 | 21.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 50,000 | 5 | 20.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht12-il | 100,000 | 9 | 26.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 100,000 | 5 | 26.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht12-il | 200,000 | 9 | 32.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 200,000 | 5 | 35.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht12-il | 500,000 | 9 | 45.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 500,000 | 5 | 50.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht12-il | 1,000,000 | 9 | 58.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 1,000,000 | 5 | 64.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe367-il | 50,000 | 9 | 5.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 50,000 | 5 | 20.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe367-il | 100,000 | 9 | 41.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 100,000 | 5 | 47.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe367-il | 200,000 | 9 | 68 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 200,000 | 5 | 64.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe367-il | 500,000 | 9 | 93.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 500,000 | 5 | 83.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe367-il | 1,000,000 | 9 | 111.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 1,000,000 | 5 | 98.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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