NACA 23012 12% (naca23012-il)
NACA 23012 12% - NACA 23012 airfoil
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(naca23012-il) NACA 23012 12% NACA 23012 airfoil Max thickness 12% at 29.8% chord. Max camber 1.8% at 12.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 23012 12% 1.00003 0.00126 0.99730 0.00170 0.98914 0.00302 0.97563 0.00518 0.95693 0.00812 0.93324 0.01176 0.90482 0.01602 0.87197 0.02079 0.83506 0.02597 0.79449 0.03145 0.75070 0.03712 0.70417 0.04285 0.65541 0.04854 0.60496 0.05405 0.55335 0.05924 0.50117 0.06397 0.44897 0.06811 0.39733 0.07150 0.34681 0.07402 0.29796 0.07554 0.25131 0.07597 0.20738 0.07524 0.16604 0.07320 0.12732 0.06915 0.09230 0.06265 0.06203 0.05382 0.03730 0.04324 0.01865 0.03176 0.00628 0.02030 0.00015 0.00956 0.00000 0.00000 0.00533 -0.00792 0.01557 -0.01401 0.03029 -0.01870 0.04915 -0.02248 0.07195 -0.02586 0.09868 -0.02922 0.12954 -0.03282 0.16483 -0.03660 0.20483 -0.04016 0.24869 -0.04283 0.29531 -0.04446 0.34418 -0.04510 0.39476 -0.04482 0.44650 -0.04371 0.49883 -0.04188 0.55117 -0.03945 0.60296 -0.03655 0.65360 -0.03327 0.70257 -0.02975 0.74930 -0.02607 0.79330 -0.02235 0.83407 -0.01866 0.87118 -0.01512 0.90420 -0.01180 0.93279 -0.00880 0.95661 -0.00621 0.97543 -0.00410 0.98901 -0.00254 0.99722 -0.00158 0.99997 -0.00126 |
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 23012 12% (naca23012-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca23012-il | 50,000 | 9 | 24.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23012-il | 50,000 | 5 | 28.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23012-il | 100,000 | 9 | 36.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23012-il | 100,000 | 5 | 40.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23012-il | 200,000 | 9 | 51 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23012-il | 200,000 | 5 | 55.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23012-il | 500,000 | 9 | 77.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23012-il | 500,000 | 5 | 77.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23012-il | 1,000,000 | 9 | 96.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23012-il | 1,000,000 | 5 | 93.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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