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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(s3025-il) S3025 9.38% | Selig S3025 low Reynolds number airfoil Max thickness 9.4% at 30.9% chord Max camber 3% at 44.9% chord | Remove Airfoil details Airfoil plotter |
(goe490-il) GOE 490 AIRFOIL | Gottingen 490 airfoil Max thickness 8.8% at 19.9% chord Max camber 3.8% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(sd7032-il) SD7032-099-88 | Selig/Donovan SD7032 low Reynolds number airfoil Max thickness 10% at 26.6% chord Max camber 3.4% at 45.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s3025-il,goe490-il,sd7032-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
---|---|---|---|---|---|---|---|
s3025-il | 50,000 | 9 | 33.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s3025-il | 50,000 | 5 | 39.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
s3025-il | 100,000 | 9 | 57 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s3025-il | 100,000 | 5 | 58.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
s3025-il | 200,000 | 9 | 80 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s3025-il | 200,000 | 5 | 77.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
s3025-il | 500,000 | 9 | 109.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s3025-il | 500,000 | 5 | 99.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
s3025-il | 1,000,000 | 9 | 130.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s3025-il | 1,000,000 | 5 | 114.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe490-il | 50,000 | 9 | 33.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe490-il | 50,000 | 5 | 38.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe490-il | 100,000 | 9 | 54.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe490-il | 100,000 | 5 | 54.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe490-il | 200,000 | 9 | 72.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe490-il | 200,000 | 5 | 70.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe490-il | 500,000 | 9 | 96.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe490-il | 500,000 | 5 | 89.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe490-il | 1,000,000 | 9 | 114.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe490-il | 1,000,000 | 5 | 98.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
sd7032-il | 50,000 | 9 | 31.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
sd7032-il | 50,000 | 5 | 39.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
sd7032-il | 100,000 | 9 | 56.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
sd7032-il | 100,000 | 5 | 58 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
sd7032-il | 200,000 | 9 | 77.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
sd7032-il | 200,000 | 5 | 75.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
sd7032-il | 500,000 | 9 | 105.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
sd7032-il | 500,000 | 5 | 97.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
sd7032-il | 1,000,000 | 9 | 125.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
sd7032-il | 1,000,000 | 5 | 114.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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