NACA 1412 (naca1412-il)
NACA 1412 - NACA 1412 airfoil
| Details | Dat file | Parser | |
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(naca1412-il) NACA 1412 NACA 1412 airfoil Max thickness 12% at 29.9% chord. Max camber 1% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 1412 1.00000 0.00126 0.95025 0.00966 0.90040 0.01753 0.80058 0.03178 0.70061 0.04413 0.60051 0.05453 0.50029 0.06267 0.40000 0.06803 0.29925 0.06940 0.24889 0.06799 0.19857 0.06486 0.14833 0.05951 0.09824 0.05118 0.07330 0.04537 0.04845 0.03786 0.02378 0.02733 0.01158 0.01954 0.00000 0.00000 0.01342 -0.01830 0.02622 -0.02491 0.05155 -0.03318 0.07670 -0.03857 0.10176 -0.04242 0.15167 -0.04733 0.20143 -0.04986 0.25111 -0.05081 0.30075 -0.05064 0.40000 -0.04803 0.49971 -0.04321 0.59949 -0.03675 0.69939 -0.02913 0.79942 -0.02066 0.89960 -0.01141 0.94975 -0.00646 1.00000 -0.00126 |
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Polars for NACA 1412 (naca1412-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca1412-il | 50,000 | 9 | 29.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 50,000 | 5 | 31.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 100,000 | 9 | 44.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 100,000 | 5 | 43 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 200,000 | 9 | 57.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 200,000 | 5 | 53.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 500,000 | 9 | 73.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 500,000 | 5 | 66 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 1,000,000 | 9 | 83.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 1,000,000 | 5 | 78.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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