HT23 (ht23-il)
HT23 - Drela HT23 airfoil
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(ht23-il) HT23 Drela HT23 airfoil Max thickness 6.5% at 20.8% chord. Max camber 1.1% at 22.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
HT23
1.000013 0.001041
0.993330 0.001400
0.981297 0.002057
0.966759 0.002850
0.950143 0.003764
0.932194 0.004762
0.913554 0.005798
0.894602 0.006866
0.875511 0.007946
0.856358 0.009031
0.837176 0.010116
0.817981 0.011207
0.798779 0.012298
0.779575 0.013395
0.760387 0.014490
0.741199 0.015592
0.722050 0.016699
0.702899 0.017805
0.683777 0.018923
0.664663 0.020042
0.645549 0.021169
0.626465 0.022303
0.607368 0.023452
0.588297 0.024613
0.569229 0.025789
0.550164 0.026978
0.531123 0.028173
0.512073 0.029372
0.493081 0.030568
0.474020 0.031761
0.454927 0.032946
0.435930 0.034112
0.416976 0.035254
0.398196 0.036360
0.379553 0.037425
0.364932 0.038231
0.355753 0.038721
0.342226 0.039418
0.322550 0.040368
0.302367 0.041245
0.282830 0.041979
0.264035 0.042557
0.245551 0.042980
0.227208 0.043233
0.209044 0.043294
0.191076 0.043139
0.173411 0.042749
0.156090 0.042105
0.139358 0.041202
0.123371 0.040040
0.108312 0.038633
0.094349 0.037010
0.081733 0.035230
0.070571 0.033362
0.060866 0.031471
0.052509 0.029606
0.045368 0.027807
0.039247 0.026086
0.033954 0.024440
0.029318 0.022854
0.025198 0.021307
0.021478 0.019785
0.018002 0.018219
0.014628 0.016518
0.011295 0.014589
0.008073 0.012378
0.005183 0.009914
0.002782 0.007204
0.000976 0.004168
0.000072 0.001086
0.000000 0.000000
0.000130 -0.001368
0.000766 -0.003131
0.001556 -0.004268
0.002293 -0.005026
0.003307 -0.005829
0.004762 -0.006736
0.006592 -0.007656
0.008703 -0.008544
0.011042 -0.009388
0.013681 -0.010216
0.016760 -0.011059
0.020407 -0.011933
0.024703 -0.012834
0.029733 -0.013750
0.035539 -0.014668
0.042186 -0.015578
0.049776 -0.016471
0.058457 -0.017344
0.068374 -0.018185
0.079706 -0.018982
0.092510 -0.019711
0.106739 -0.020351
0.122111 -0.020878
0.138375 -0.021282
0.155243 -0.021566
0.172587 -0.021738
0.190252 -0.021811
0.208211 -0.021795
0.226364 -0.021704
0.244744 -0.021547
0.263506 -0.021339
0.282800 -0.021080
0.302831 -0.020767
0.323757 -0.020398
0.346109 -0.019962
0.357456 -0.019726
0.371368 -0.019424
0.387020 -0.019070
0.404566 -0.018654
0.422199 -0.018219
0.440148 -0.017761
0.458343 -0.017282
0.476758 -0.016786
0.495345 -0.016274
0.513975 -0.015755
0.532605 -0.015228
0.551227 -0.014695
0.569832 -0.014156
0.588454 -0.013610
0.607140 -0.013053
0.625909 -0.012488
0.644822 -0.011912
0.663939 -0.011329
0.683165 -0.010738
0.702394 -0.010138
0.721621 -0.009536
0.740849 -0.008939
0.760077 -0.008337
0.779305 -0.007742
0.798532 -0.007145
0.817756 -0.006551
0.836972 -0.005952
0.856175 -0.005360
0.875350 -0.004764
0.894463 -0.004176
0.913435 -0.003596
0.932096 -0.003031
0.950064 -0.002497
0.966698 -0.002009
0.981250 -0.001579
0.993298 -0.001235
0.999987 -0.001041
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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 HT23 (ht23-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ht23-il | 50,000 | 9 | 24.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 50,000 | 5 | 29 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 100,000 | 9 | 37.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 100,000 | 5 | 39.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 200,000 | 9 | 50.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 200,000 | 5 | 50.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 500,000 | 9 | 67.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 500,000 | 5 | 65.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 1,000,000 | 9 | 79.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 1,000,000 | 5 | 79.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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