NACA 0012-64 (naca001264-il)
NACA 0012-64 - NACA 0012-64 airfoil
| Details | Dat file | Parser | |
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(naca001264-il) NACA 0012-64 NACA 0012-64 airfoil Max thickness 12% at 40% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 0012-64 1.0000 0.00120 0.9500 0.01027 0.9000 0.01867 0.8000 0.03320 0.7000 0.04480 0.6000 0.05320 0.5000 0.05827 0.4000 0.06000 0.3000 0.05827 0.2000 0.05293 0.1500 0.04867 0.1000 0.04240 0.0750 0.03813 0.0500 0.03267 0.0250 0.02453 0.0125 0.01813 0.0000 0.00000 0.0125 -0.01813 0.0250 -0.02453 0.0500 -0.03267 0.0750 -0.03813 0.1000 -0.04240 0.1500 -0.04867 0.2000 -0.05293 0.3000 -0.05827 0.4000 -0.06000 0.5000 -0.05827 0.6000 -0.05320 0.7000 -0.04480 0.8000 -0.03320 0.9000 -0.01867 0.9500 -0.01027 1.0000 -0.00120 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for NACA 0012-64 (naca001264-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca001264-il | 50,000 | 9 | 26.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264-il | 50,000 | 5 | 25.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001264-il | 100,000 | 9 | 37.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264-il | 100,000 | 5 | 32.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001264-il | 200,000 | 9 | 43.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264-il | 200,000 | 5 | 40.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001264-il | 500,000 | 9 | 50.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264-il | 500,000 | 5 | 53.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001264-il | 1,000,000 | 9 | 63 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264-il | 1,000,000 | 5 | 67.8 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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