HT08 (ht08-il)
HT08 - Drela HT08 airfoil
| Details | Dat file | Parser | |
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(ht08-il) HT08 Drela HT08 airfoil Max thickness 5% at 20.2% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
HT08
1.000000 0.001737
0.994321 0.001978
0.983001 0.002455
0.969574 0.003016
0.955502 0.003596
0.941297 0.004176
0.927068 0.004749
0.912833 0.005316
0.898597 0.005876
0.884359 0.006429
0.870120 0.006976
0.855880 0.007517
0.841636 0.008053
0.827389 0.008584
0.813142 0.009111
0.798895 0.009633
0.784648 0.010151
0.770402 0.010665
0.756156 0.011174
0.741911 0.011678
0.727666 0.012177
0.713421 0.012671
0.699177 0.013159
0.684933 0.013642
0.670689 0.014119
0.656445 0.014590
0.642202 0.015056
0.627958 0.015516
0.613715 0.015969
0.599471 0.016417
0.585228 0.016858
0.570985 0.017294
0.556742 0.017723
0.542499 0.018145
0.528255 0.018562
0.514012 0.018972
0.499769 0.019375
0.485526 0.019772
0.471283 0.020162
0.457041 0.020545
0.442800 0.020922
0.428562 0.021290
0.414325 0.021650
0.400091 0.022001
0.385861 0.022342
0.371635 0.022672
0.357415 0.022989
0.343200 0.023292
0.328992 0.023580
0.314791 0.023849
0.300599 0.024098
0.286417 0.024325
0.272246 0.024526
0.258089 0.024698
0.243947 0.024837
0.229823 0.024940
0.215722 0.024999
0.201646 0.025010
0.187601 0.024964
0.173590 0.024854
0.159616 0.024671
0.145687 0.024405
0.131813 0.024045
0.118016 0.023578
0.104325 0.022984
0.090777 0.022238
0.077423 0.021310
0.064341 0.020163
0.051699 0.018768
0.039864 0.017111
0.029454 0.015241
0.021094 0.013312
0.014881 0.011485
0.010371 0.009805
0.007047 0.008240
0.004556 0.006739
0.002689 0.005254
0.001339 0.003754
0.000466 0.002237
0.000049 0.000734
0.000049 -0.000710
0.000466 -0.002213
0.001339 -0.003731
0.002689 -0.005230
0.004556 -0.006715
0.007047 -0.008217
0.010371 -0.009781
0.014881 -0.011461
0.021094 -0.013289
0.029453 -0.015218
0.039863 -0.017088
0.051698 -0.018745
0.064341 -0.020141
0.077422 -0.021287
0.090776 -0.022216
0.104324 -0.022962
0.118015 -0.023557
0.131812 -0.024024
0.145686 -0.024384
0.159615 -0.024651
0.173589 -0.024834
0.187600 -0.024944
0.201645 -0.024990
0.215721 -0.024980
0.229822 -0.024921
0.243946 -0.024819
0.258088 -0.024680
0.272246 -0.024508
0.286417 -0.024307
0.300599 -0.024081
0.314791 -0.023832
0.328991 -0.023563
0.343199 -0.023276
0.357414 -0.022973
0.371635 -0.022656
0.385861 -0.022327
0.400091 -0.021986
0.414324 -0.021635
0.428561 -0.021275
0.442800 -0.020907
0.457040 -0.020532
0.471282 -0.020149
0.485525 -0.019759
0.499768 -0.019362
0.514012 -0.018959
0.528255 -0.018549
0.542498 -0.018133
0.556741 -0.017711
0.570984 -0.017282
0.585228 -0.016847
0.599471 -0.016406
0.613714 -0.015959
0.627958 -0.015505
0.642201 -0.015046
0.656445 -0.014581
0.670689 -0.014110
0.684933 -0.013633
0.699177 -0.013150
0.713421 -0.012663
0.727666 -0.012169
0.741911 -0.011671
0.756156 -0.011167
0.770402 -0.010658
0.784648 -0.010145
0.798895 -0.009627
0.813142 -0.009104
0.827389 -0.008578
0.841636 -0.008047
0.855879 -0.007512
0.870120 -0.006971
0.884359 -0.006425
0.898597 -0.005872
0.912833 -0.005312
0.927068 -0.004746
0.941297 -0.004173
0.955502 -0.003593
0.969573 -0.003013
0.983000 -0.002453
0.994321 -0.001976
1.000000 -0.001735
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Similar airfoils
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Polars for HT08 (ht08-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ht08-il | 50,000 | 9 | 21.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht08-il | 50,000 | 5 | 20.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht08-il | 100,000 | 9 | 28.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht08-il | 100,000 | 5 | 26.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht08-il | 200,000 | 9 | 33.1 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht08-il | 200,000 | 5 | 34.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht08-il | 500,000 | 9 | 44.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht08-il | 500,000 | 5 | 48.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht08-il | 1,000,000 | 9 | 56.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht08-il | 1,000,000 | 5 | 63.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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