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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(hq1585-il) HQ 1.5/8.5 AIRFOIL | Quabeck HQ 1.5/8.5 R/C sailplane airfoil Max thickness 8.6% at 35% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(s1223-il) S1223 | Selig S1223 high lift low Reynolds number airfoil Max thickness 12.1% at 19.8% chord Max camber 8.1% at 49% chord | Remove Airfoil details Airfoil plotter |
(m27-il) NACA M27 AIRFOIL | NACA/Munk M-27 airfoil Max thickness 12% at 30.1% chord Max camber 8.4% at 30.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq1585-il,s1223-il,m27-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
---|---|---|---|---|---|---|---|
hq1585-il | 50,000 | 9 | 35.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
hq1585-il | 50,000 | 5 | 35.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
hq1585-il | 100,000 | 9 | 51.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
hq1585-il | 100,000 | 5 | 48.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
hq1585-il | 200,000 | 9 | 67.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
hq1585-il | 200,000 | 5 | 58.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
hq1585-il | 500,000 | 9 | 84.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
hq1585-il | 500,000 | 5 | 67.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
hq1585-il | 1,000,000 | 9 | 85.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
hq1585-il | 1,000,000 | 5 | 80.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
s1223-il | 50,000 | 9 | 33.1 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s1223-il | 50,000 | 5 | 42.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
s1223-il | 100,000 | 9 | 54.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s1223-il | 100,000 | 5 | 59.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
s1223-il | 200,000 | 9 | 73.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s1223-il | 200,000 | 5 | 75.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
s1223-il | 500,000 | 9 | 98.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s1223-il | 500,000 | 5 | 97.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
s1223-il | 1,000,000 | 9 | 121.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
s1223-il | 1,000,000 | 5 | 120 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
m27-il | 50,000 | 9 | 4.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
m27-il | 50,000 | 5 | 9.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
m27-il | 100,000 | 9 | 9 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
m27-il | 100,000 | 5 | 41.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
m27-il | 200,000 | 9 | 62.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
m27-il | 200,000 | 5 | 70.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
m27-il | 500,000 | 9 | 105.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
m27-il | 500,000 | 5 | 105 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
m27-il | 1,000,000 | 9 | 135.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
m27-il | 1,000,000 | 5 | 126.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
Reynolds number calculator |