NACA 67 (naca671215-il)
NACA 67 - NACA 67
| Details | Dat file | Parser | |
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(naca671215-il) NACA 67 NACA 67 Max thickness 15% at 50% chord. Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 67,1-215 1.00000 0.00000 0.95037 0.01103 0.90071 0.02537 0.85092 0.03999 0.80100 0.05335 0.75098 0.06515 0.70086 0.07373 0.65068 0.07935 0.60047 0.08302 0.55024 0.08516 0.50000 0.08600 0.44976 0.08570 0.39953 0.08430 0.34930 0.08185 0.29908 0.07825 0.24887 0.07348 0.19869 0.06735 0.14854 0.05954 0.09845 0.04947 0.07344 0.04321 0.04848 0.03557 0.02361 0.02577 0.01128 0.01867 0.00642 0.01460 0.00402 0.01213 0.00000 0.00000 0.00598 -0.01113 0.00858 -0.01320 0.01372 -0.01653 0.02639 -0.02205 0.05152 -0.02925 0.07656 -0.03473 0.10155 -0.03913 0.15146 -0.04608 0.20131 -0.05143 0.25113 -0.05558 0.30092 -0.05881 0.35070 -0.06125 0.40047 -0.06288 0.45024 -0.06380 0.50000 -0.06394 0.54976 -0.06326 0.59953 -0.06160 0.64932 -0.05875 0.69914 -0.05429 0.74902 -0.04725 0.79900 -0.03743 0.84908 -0.02653 0.89929 -0.01503 0.94963 -0.00471 1.00000 0.00000 |
Dat file parser warnings
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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 67 (naca671215-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca671215-il | 50,000 | 9 | 23.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca671215-il | 50,000 | 5 | 21.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca671215-il | 100,000 | 9 | 34.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca671215-il | 100,000 | 5 | 25.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca671215-il | 200,000 | 9 | 42.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca671215-il | 200,000 | 5 | 33.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca671215-il | 500,000 | 9 | 56.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca671215-il | 500,000 | 5 | 55.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca671215-il | 1,000,000 | 9 | 84.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca671215-il | 1,000,000 | 5 | 71.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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