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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(ag16-il) AG16 | Drela AG16 airfoil Max thickness 7.1% at 23.4% chord Max camber 1.9% at 46.9% chord | Remove Airfoil details Airfoil plotter |
(ls421-il) NASA/LANGLEY LS(1)-0421 AIRFOIL | NASA/Langley LS(1)-0421 general aviation airfoil Max thickness 20.9% at 40% chord Max camber 2.4% at 65% chord | Remove Airfoil details Airfoil plotter |
(tsagi-r-3a-il) TsAGI R-3a (12%) | TsAGI R-3a used on Russian ultra light aircraft (12%). Max thickness 12.1% at 23.1% chord Max camber 3.1% at 24.1% chord | Remove Airfoil details Airfoil plotter |
(clarky-il) CLARK Y AIRFOIL | CLARK Y airfoil Max thickness 11.7% at 28% chord Max camber 3.4% at 42% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag16-il,ls421-il,tsagi-r-3a-il,clarky-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag16-il | 50,000 | 9 | 33.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag16-il | 50,000 | 5 | 36 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag16-il | 100,000 | 9 | 48.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag16-il | 100,000 | 5 | 48.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag16-il | 200,000 | 9 | 63.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag16-il | 200,000 | 5 | 60.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag16-il | 500,000 | 9 | 82.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag16-il | 500,000 | 5 | 76.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag16-il | 1,000,000 | 9 | 95.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag16-il | 1,000,000 | 5 | 88.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421-il | 50,000 | 9 | 23.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 50,000 | 5 | 18.4 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421-il | 100,000 | 9 | 33.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 100,000 | 5 | 30.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421-il | 200,000 | 9 | 52.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 200,000 | 5 | 56.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421-il | 500,000 | 9 | 89.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 500,000 | 5 | 81.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421-il | 1,000,000 | 9 | 111.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 1,000,000 | 5 | 91.2 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 50,000 | 9 | 16.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 50,000 | 5 | 25.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 100,000 | 9 | 33 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 100,000 | 5 | 43.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 200,000 | 9 | 56.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 200,000 | 5 | 60.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 500,000 | 9 | 86.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 500,000 | 5 | 88.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 1,000,000 | 9 | 112.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 1,000,000 | 5 | 108.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 50,000 | 9 | 29.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 50,000 | 5 | 36.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 100,000 | 9 | 53 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 100,000 | 5 | 54.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 200,000 | 9 | 73.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 200,000 | 5 | 69.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 500,000 | 9 | 98.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 500,000 | 5 | 90.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 1,000,000 | 9 | 114.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 1,000,000 | 5 | 108.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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