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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(du8608418-il) DU86-084/18 8.44% | Deflt University DU 86-084/18 low Reynolds number airfoil Max thickness 8.5% at 36.9% chord Max camber 1% at 45.8% chord | Remove Airfoil details Airfoil plotter |
(fx78k161-il) FX 78-K-161 | Wortmann FX 78-K-161 airfoil for use with flaps (K) Max thickness 16.2% at 40.2% chord Max camber 2.8% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(naca16018-il) NACA 16-018 | NACA 16-018 airfoil Max thickness 18% at 50% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (du8608418-il,fx78k161-il,naca16018-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| du8608418-il | 50,000 | 9 | 32.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 50,000 | 5 | 31.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du8608418-il | 100,000 | 9 | 46.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 100,000 | 5 | 43.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du8608418-il | 200,000 | 9 | 63.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 200,000 | 5 | 53.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du8608418-il | 500,000 | 9 | 75.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 500,000 | 5 | 59.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du8608418-il | 1,000,000 | 9 | 71 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 1,000,000 | 5 | 70.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k161-il | 50,000 | 9 | 15.1 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k161-il | 50,000 | 5 | 13.4 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k161-il | 100,000 | 9 | 23.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k161-il | 100,000 | 5 | 24.5 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k161-il | 200,000 | 9 | 65.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k161-il | 200,000 | 5 | 43.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k161-il | 500,000 | 9 | 81.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k161-il | 500,000 | 5 | 81 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k161-il | 1,000,000 | 9 | 102.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k161-il | 1,000,000 | 5 | 98.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16018-il | 50,000 | 9 | 22.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16018-il | 50,000 | 5 | 20.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16018-il | 100,000 | 9 | 28.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16018-il | 100,000 | 5 | 24.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16018-il | 200,000 | 9 | 37.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16018-il | 200,000 | 5 | 30 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16018-il | 500,000 | 9 | 44.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16018-il | 500,000 | 5 | 33.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16018-il | 1,000,000 | 9 | 47.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16018-il | 1,000,000 | 5 | 40.5 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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