NACA 0006 (naca0006-il)
NACA 0006 - NACA 0006 airfoil
| Details | Dat file | Parser | |
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(naca0006-il) NACA 0006 NACA 0006 airfoil Max thickness 6% at 30% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 0006 1.0000 0.00063 0.9500 0.00403 0.9000 0.00724 0.8000 0.01312 0.7000 0.01832 0.6000 0.02282 0.5000 0.02647 0.4000 0.02902 0.3000 0.03001 0.2500 0.02971 0.2000 0.02869 0.1500 0.02673 0.1000 0.02341 0.0750 0.02100 0.0500 0.01777 0.0250 0.01307 0.0125 0.00947 0.0000 0.00000 0.0125 -0.00947 0.0250 -0.01307 0.0500 -0.01777 0.0750 -0.02100 0.1000 -0.02341 0.1500 -0.02673 0.2000 -0.02869 0.2500 -0.02971 0.3000 -0.03001 0.4000 -0.02902 0.5000 -0.02647 0.6000 -0.02282 0.7000 -0.01832 0.8000 -0.01312 0.9000 -0.00724 0.9500 -0.00403 1.0000 -0.00063 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
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Polars for NACA 0006 (naca0006-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca0006-il | 50,000 | 9 | 24.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0006-il | 50,000 | 5 | 22.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0006-il | 100,000 | 9 | 32.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0006-il | 100,000 | 5 | 27.3 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0006-il | 200,000 | 9 | 38.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0006-il | 200,000 | 5 | 34 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0006-il | 500,000 | 5 | 47.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0006-il | 1,000,000 | 9 | 56.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0006-il | 1,000,000 | 5 | 60.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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