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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(m17-il) NACA M17 AIRFOIL | NACA/Munk M-17 airfoil Max thickness 8.1% at 40% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
(lds2-il) LDS-2 AIRFOIL | LDS-2 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 45% chord | Remove Airfoil details Airfoil plotter |
(l188tip-il) LOCKHEED L-188 TIP AIRFOIL | Lockheed L-188/P-3 tip airfoil NACA 0012 -1.10 40/1.051 Cli=.4 a=.8 Max thickness 12% at 41.3% chord Max camber 2.7% at 51.7% chord | Remove Airfoil details Airfoil plotter |
(l7769-il) LISSAMAN 7769 AIRFOIL | Lissaman 7769 human powered aircraft airfoil Max thickness 11% at 30% chord Max camber 4.4% at 30% chord | Remove Airfoil details Airfoil plotter |
(ls413-il) NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL | NASA/Langley LS(1)-0413 (GA(W)-2) general aviation airfoil Max thickness 12.9% at 37.5% chord Max camber 2.4% at 65% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m17-il,lds2-il,l188tip-il,l7769-il,ls413-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
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m17-il | 50,000 | 9 | 35.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
m17-il | 50,000 | 5 | 35.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
m17-il | 100,000 | 9 | 55.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
m17-il | 100,000 | 5 | 55.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
m17-il | 200,000 | 9 | 75.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
m17-il | 200,000 | 5 | 74.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
m17-il | 500,000 | 9 | 102.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
m17-il | 500,000 | 5 | 98.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
m17-il | 1,000,000 | 9 | 122.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
m17-il | 1,000,000 | 5 | 114.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
lds2-il | 50,000 | 9 | 34 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
lds2-il | 50,000 | 5 | 33.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
lds2-il | 100,000 | 9 | 52.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
lds2-il | 100,000 | 5 | 50.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
lds2-il | 200,000 | 9 | 72.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
lds2-il | 200,000 | 5 | 66.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
lds2-il | 500,000 | 9 | 97.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
lds2-il | 500,000 | 5 | 77.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
lds2-il | 1,000,000 | 9 | 106.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
lds2-il | 1,000,000 | 5 | 85.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
l188tip-il | 50,000 | 9 | 35.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
l188tip-il | 50,000 | 5 | 33.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
l188tip-il | 100,000 | 9 | 55.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
l188tip-il | 100,000 | 5 | 53.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
l188tip-il | 200,000 | 9 | 79.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
l188tip-il | 200,000 | 5 | 72.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
l188tip-il | 500,000 | 9 | 109 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
l188tip-il | 500,000 | 5 | 91.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
l188tip-il | 1,000,000 | 9 | 127 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
l188tip-il | 1,000,000 | 5 | 93.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
l7769-il | 50,000 | 9 | 6.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
l7769-il | 50,000 | 5 | 15.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
l7769-il | 100,000 | 9 | 32.3 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
l7769-il | 100,000 | 5 | 39.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
l7769-il | 200,000 | 9 | 72.6 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
l7769-il | 200,000 | 5 | 74.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
l7769-il | 500,000 | 9 | 113.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
l7769-il | 500,000 | 5 | 111 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
l7769-il | 1,000,000 | 9 | 143.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
l7769-il | 1,000,000 | 5 | 136.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
ls413-il | 50,000 | 9 | 35.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
ls413-il | 50,000 | 5 | 33.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
ls413-il | 100,000 | 9 | 53 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
ls413-il | 100,000 | 5 | 48.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
ls413-il | 200,000 | 9 | 69.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
ls413-il | 200,000 | 5 | 65.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
ls413-il | 500,000 | 9 | 96.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
ls413-il | 500,000 | 5 | 82.5 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
ls413-il | 1,000,000 | 9 | 112.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
ls413-il | 1,000,000 | 5 | 86.4 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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