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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(n6409-il) NACA6409 9% | NACA 6409 Max thickness 9% at 29.3% chord Max camber 6% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(s1010-il) S1010 HPV airfoil | Selig S1010 HPV airfoil Max thickness 6% at 23.3% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(s4180-il) S4180-098-84 | Selig S4180 low Reynolds number airfoil Max thickness 9.8% at 26.1% chord Max camber 4% at 39.4% chord | Remove Airfoil details Airfoil plotter |
(s5010-il) S5010 | Selig S5010 low Reynolds number airfoil Max thickness 9.8% at 27.6% chord Max camber 1.8% at 32% chord | Remove Airfoil details Airfoil plotter |
(s8036-il) S8036 (16%) | Selig S8036 low Reynolds number airfoil Max thickness 16% at 36.8% chord Max camber 1.3% at 40.4% 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 |
(ht05-il) HT05 | Drela HT05 airfoil Max thickness 4.8% at 17.1% chord Max camber 0% at 63.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n6409-il,s1010-il,s4180-il,s5010-il,s8036-il,ht12-il,ht05-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n6409-il | 50,000 | 9 | 27.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 50,000 | 5 | 36 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 100,000 | 9 | 61.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 100,000 | 5 | 63.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 200,000 | 9 | 87.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 200,000 | 5 | 87.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 500,000 | 9 | 122.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 500,000 | 5 | 118.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 1,000,000 | 9 | 151 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 1,000,000 | 5 | 144.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1010-il | 50,000 | 9 | 20.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1010-il | 50,000 | 5 | 21.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1010-il | 100,000 | 9 | 29.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1010-il | 100,000 | 5 | 29.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1010-il | 200,000 | 9 | 37.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1010-il | 200,000 | 5 | 40.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1010-il | 500,000 | 9 | 53.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1010-il | 500,000 | 5 | 55.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1010-il | 1,000,000 | 9 | 66.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1010-il | 1,000,000 | 5 | 69.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 50,000 | 9 | 28.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 50,000 | 5 | 37.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 100,000 | 9 | 55.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 100,000 | 5 | 58.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 200,000 | 9 | 78.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 200,000 | 5 | 78.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 500,000 | 9 | 110.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 500,000 | 5 | 104.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 1,000,000 | 9 | 133.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 1,000,000 | 5 | 122.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 50,000 | 9 | 24.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 50,000 | 5 | 32.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 100,000 | 9 | 45 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 100,000 | 5 | 47.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 200,000 | 9 | 63.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 200,000 | 5 | 62.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 500,000 | 9 | 86.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 500,000 | 5 | 80.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 1,000,000 | 9 | 102.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 1,000,000 | 5 | 94.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 50,000 | 9 | 26.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 50,000 | 5 | 25.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 100,000 | 9 | 48.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 100,000 | 5 | 48 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 200,000 | 9 | 70.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 200,000 | 5 | 61.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 500,000 | 9 | 87.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 500,000 | 5 | 73.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 1,000,000 | 9 | 99.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 1,000,000 | 5 | 82.1 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 | |
| ht05-il | 50,000 | 9 | 19.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 50,000 | 5 | 19.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 100,000 | 9 | 24.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 100,000 | 5 | 26.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 200,000 | 9 | 31.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 200,000 | 5 | 34.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 500,000 | 9 | 44.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 500,000 | 5 | 49.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 1,000,000 | 9 | 57.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 1,000,000 | 5 | 63.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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