NACA 16-006 (naca16006-il)
NACA 16-006 - NACA 16-006 airfoil
| Details | Dat file | Parser | |
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(naca16006-il) NACA 16-006 NACA 16-006 airfoil Max thickness 6% at 50% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 16-006 1.0000 0.00060 0.9500 0.00707 0.9000 0.01259 0.8000 0.02099 0.7000 0.02635 0.6000 0.02917 0.5000 0.03000 0.4000 0.02927 0.3000 0.02709 0.2000 0.02332 0.1500 0.02067 0.1000 0.01729 0.0750 0.01516 0.0500 0.01255 0.0250 0.00903 0.0125 0.00646 0.0000 0.00000 0.0125 -0.00646 0.0250 -0.00903 0.0500 -0.01255 0.0750 -0.01516 0.1000 -0.01729 0.1500 -0.02067 0.2000 -0.02332 0.3000 -0.02709 0.4000 -0.02927 0.5000 -0.03000 0.6000 -0.02917 0.7000 -0.02635 0.8000 -0.02099 0.9000 -0.01259 0.9500 -0.00707 1.0000 -0.00060 |
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Polars for NACA 16-006 (naca16006-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca16006-il | 50,000 | 9 | 16.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 50,000 | 5 | 16.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16006-il | 100,000 | 9 | 20.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 100,000 | 5 | 21.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16006-il | 200,000 | 9 | 25.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 200,000 | 5 | 33.4 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16006-il | 500,000 | 9 | 41.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 500,000 | 5 | 34 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16006-il | 1,000,000 | 9 | 40.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 1,000,000 | 5 | 36.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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