NACA 6412 (naca6412-il)
NACA 6412 - NACA 6412 airfoil
| Details | Dat file | Parser | |
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(naca6412-il) NACA 6412 NACA 6412 airfoil Max thickness 12% at 30.1% chord. Max camber 6% at 39.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 6412
1.00025 0.00124
0.99758 0.00216
0.98961 0.00490
0.97640 0.00935
0.95808 0.01538
0.93481 0.02278
0.90682 0.03130
0.87436 0.04068
0.83777 0.05062
0.79740 0.06082
0.75366 0.07097
0.70702 0.08079
0.65797 0.08998
0.60703 0.09827
0.55477 0.10543
0.50176 0.11124
0.44863 0.11554
0.39587 0.11817
0.34306 0.11841
0.29199 0.11583
0.24336 0.11060
0.19780 0.10302
0.15592 0.09344
0.11825 0.08231
0.08524 0.07012
0.05726 0.05736
0.03460 0.04452
0.01745 0.03204
0.00595 0.02029
0.00014 0.00955
0.00000 0.00000
0.00534 -0.00792
0.01590 -0.01383
0.03149 -0.01781
0.05186 -0.01999
0.07672 -0.02054
0.10574 -0.01967
0.13861 -0.01763
0.17495 -0.01470
0.21441 -0.01121
0.25664 -0.00748
0.30127 -0.00384
0.34792 -0.00064
0.39622 0.00182
0.44685 0.00370
0.49824 0.00542
0.54976 0.00684
0.60088 0.00786
0.65105 0.00843
0.69972 0.00853
0.74634 0.00819
0.79039 0.00747
0.83137 0.00643
0.86878 0.00520
0.90220 0.00386
0.93121 0.00252
0.95546 0.00129
0.97465 0.00024
0.98854 -0.00057
0.99694 -0.00107
0.99975 -0.00124
1.00000 0.00000
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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 6412 (naca6412-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca6412-il | 50,000 | 9 | 9.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca6412-il | 50,000 | 5 | 29.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca6412-il | 100,000 | 9 | 53.1 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca6412-il | 100,000 | 5 | 58.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca6412-il | 200,000 | 9 | 80 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca6412-il | 200,000 | 5 | 81.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca6412-il | 500,000 | 9 | 114.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca6412-il | 500,000 | 5 | 111.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca6412-il | 1,000,000 | 9 | 142.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca6412-il | 1,000,000 | 5 | 136.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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