HT12 (ht12-il)
HT12 - Drela HT12 airfoil
| Details | Dat file | Parser | |
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(ht12-il) HT12 Drela HT12 airfoil Max thickness 5% at 18.6% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
HT12
1.000020 0.001191
0.993423 0.001393
0.980225 0.001798
0.964551 0.002278
0.948134 0.002780
0.931565 0.003286
0.914968 0.003793
0.898366 0.004299
0.881764 0.004806
0.865159 0.005312
0.848556 0.005816
0.831953 0.006320
0.815348 0.006824
0.798744 0.007327
0.782140 0.007829
0.765535 0.008330
0.748931 0.008830
0.732326 0.009329
0.715722 0.009828
0.699117 0.010325
0.682513 0.010821
0.665908 0.011314
0.649303 0.011808
0.632699 0.012301
0.616095 0.012792
0.599490 0.013281
0.582887 0.013769
0.566283 0.014255
0.549680 0.014740
0.533078 0.015223
0.516479 0.015703
0.499882 0.016182
0.483286 0.016658
0.466694 0.017218
0.450102 0.017785
0.433508 0.018355
0.416912 0.018929
0.400311 0.019504
0.383704 0.020080
0.367094 0.020655
0.350490 0.021226
0.333900 0.021786
0.317329 0.022332
0.300785 0.022857
0.284271 0.023352
0.267794 0.023810
0.251359 0.024218
0.234968 0.024564
0.218625 0.024838
0.202334 0.025024
0.186098 0.025114
0.169920 0.025090
0.153812 0.024939
0.137786 0.024646
0.121867 0.024191
0.106094 0.023553
0.090528 0.022704
0.075278 0.021606
0.060558 0.020225
0.046776 0.018534
0.034610 0.016575
0.024801 0.014519
0.017492 0.012547
0.012184 0.010726
0.008276 0.009024
0.005349 0.007390
0.003156 0.005769
0.001571 0.004128
0.000546 0.002462
0.000057 0.000808
0.000001 0.000014
0.000057 -0.000780
0.000546 -0.002434
0.001571 -0.004100
0.003156 -0.005741
0.005349 -0.007362
0.008276 -0.008997
0.012184 -0.010699
0.017492 -0.012519
0.024801 -0.014492
0.034609 -0.016548
0.046775 -0.018507
0.060557 -0.020199
0.075276 -0.021580
0.090527 -0.022678
0.106093 -0.023528
0.121866 -0.024167
0.137786 -0.024622
0.153811 -0.024915
0.169919 -0.025066
0.186097 -0.025091
0.202333 -0.025002
0.218625 -0.024816
0.234968 -0.024542
0.251358 -0.024196
0.267793 -0.023789
0.284271 -0.023332
0.300784 -0.022837
0.317329 -0.022312
0.333900 -0.021767
0.350490 -0.021207
0.367093 -0.020637
0.383704 -0.020062
0.400310 -0.019486
0.416911 -0.018912
0.433508 -0.018338
0.450101 -0.017769
0.466694 -0.017203
0.483286 -0.016642
0.499882 -0.016167
0.516478 -0.015688
0.533078 -0.015209
0.549679 -0.014726
0.566283 -0.014242
0.582887 -0.013756
0.599490 -0.013269
0.616094 -0.012780
0.632699 -0.012289
0.649303 -0.011797
0.665908 -0.011304
0.682513 -0.010811
0.699117 -0.010315
0.715722 -0.009818
0.732326 -0.009320
0.748931 -0.008822
0.765535 -0.008322
0.782140 -0.007821
0.798744 -0.007319
0.815347 -0.006818
0.831952 -0.006314
0.848556 -0.005810
0.865159 -0.005306
0.881763 -0.004801
0.898366 -0.004295
0.914968 -0.003789
0.931565 -0.003283
0.948134 -0.002777
0.964551 -0.002275
0.980225 -0.001796
0.993423 -0.001391
1.000020 -0.001189
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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 HT12 (ht12-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ht12-il | 50,000 | 9 | 21.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 50,000 | 5 | 20.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht12-il | 100,000 | 9 | 26.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 100,000 | 5 | 26.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht12-il | 200,000 | 9 | 32.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 200,000 | 5 | 35.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht12-il | 500,000 | 9 | 45.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 500,000 | 5 | 50.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht12-il | 1,000,000 | 9 | 58.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 1,000,000 | 5 | 64.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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