NACA 0008 (naca0008-il)
NACA 0008 - NACA 0008 airfoil
| Details | Dat file | Parser | |
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(naca0008-il) NACA 0008 NACA 0008 airfoil Max thickness 8% 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 0008 1.0000 0.00084 0.9500 0.00537 0.9000 0.00965 0.8000 0.01749 0.7000 0.02443 0.6000 0.03043 0.5000 0.03529 0.4000 0.03869 0.3000 0.04001 0.2500 0.03961 0.2000 0.03825 0.1500 0.03564 0.1000 0.03121 0.0750 0.02800 0.0500 0.02369 0.0250 0.01743 0.0125 0.01263 0.0000 0.00000 0.0125 -0.01263 0.0250 -0.01743 0.0500 -0.02369 0.0750 -0.02800 0.1000 -0.03121 0.1500 -0.03564 0.2000 -0.03825 0.2500 -0.03961 0.3000 -0.04001 0.4000 -0.03869 0.5000 -0.03529 0.6000 -0.03043 0.7000 -0.02443 0.8000 -0.01749 0.9000 -0.00965 0.9500 -0.00537 1.0000 -0.00084 |
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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 0008 (naca0008-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca0008-il | 50,000 | 9 | 26.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 50,000 | 5 | 24.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0008-il | 100,000 | 9 | 34.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 100,000 | 5 | 30.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0008-il | 200,000 | 9 | 41.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 200,000 | 5 | 38.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0008-il | 500,000 | 9 | 50.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 500,000 | 5 | 56.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0008-il | 1,000,000 | 9 | 68.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 1,000,000 | 5 | 69.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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