HT05 (ht05-il)
HT05 - Drela HT05 airfoil
| Details | Dat file | Parser | |
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(ht05-il) HT05 Drela HT05 airfoil Max thickness 4.8% at 17.1% chord. Max camber 0% at 63.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
HT05
1.000000 0.001801
0.996032 0.002100
0.983139 0.003111
0.970241 0.004063
0.957338 0.004962
0.944435 0.005811
0.931531 0.006614
0.918623 0.007376
0.905712 0.008099
0.892802 0.008784
0.879895 0.009434
0.866986 0.010052
0.854082 0.010638
0.841185 0.011195
0.828289 0.011711
0.815397 0.012164
0.802513 0.012552
0.789659 0.012870
0.776802 0.013115
0.763940 0.013276
0.751071 0.013358
0.738193 0.013360
0.725313 0.013282
0.712429 0.013127
0.699539 0.012901
0.686650 0.012602
0.673760 0.012238
0.660873 0.011810
0.647983 0.011320
0.637643 0.010884
0.632642 0.010659
0.630142 0.010545
0.627483 0.010715
0.622164 0.011053
0.609518 0.011814
0.596630 0.012540
0.583740 0.013219
0.570852 0.013855
0.557963 0.014451
0.545083 0.015020
0.532213 0.015559
0.519369 0.016076
0.506538 0.016567
0.493693 0.017041
0.480826 0.017496
0.467897 0.017936
0.454937 0.018362
0.441952 0.018773
0.428961 0.019170
0.415972 0.019553
0.402988 0.019921
0.390006 0.020273
0.377036 0.020613
0.364080 0.020941
0.351151 0.021253
0.338231 0.021556
0.325325 0.021848
0.312435 0.022127
0.299551 0.022396
0.286678 0.022654
0.273814 0.022897
0.260959 0.023125
0.248102 0.023337
0.235245 0.023531
0.222389 0.023703
0.209522 0.023851
0.196646 0.023965
0.183777 0.024040
0.170915 0.024068
0.158072 0.024037
0.145260 0.023935
0.132466 0.023751
0.119700 0.023467
0.107001 0.023063
0.094402 0.022517
0.082002 0.021807
0.069834 0.020906
0.057913 0.019777
0.046208 0.018367
0.034920 0.016611
0.024439 0.014453
0.015600 0.011990
0.009506 0.009653
0.005818 0.007724
0.003521 0.006112
0.002004 0.004665
0.000981 0.003303
0.000336 0.001952
0.000034 0.000626
0.000000 0.000012
0.000034 -0.000602
0.000336 -0.001928
0.000980 -0.003278
0.002004 -0.004641
0.003521 -0.006088
0.005818 -0.007700
0.009505 -0.009629
0.015600 -0.011967
0.024439 -0.014430
0.034920 -0.016588
0.046207 -0.018343
0.057912 -0.019754
0.069834 -0.020883
0.082002 -0.021785
0.094401 -0.022495
0.107001 -0.023042
0.119700 -0.023445
0.132465 -0.023730
0.145260 -0.023915
0.158071 -0.024016
0.170915 -0.024047
0.183776 -0.024020
0.196646 -0.023946
0.209522 -0.023831
0.222389 -0.023684
0.235244 -0.023512
0.248101 -0.023318
0.260958 -0.023107
0.273814 -0.022879
0.286677 -0.022636
0.299551 -0.022379
0.312434 -0.022110
0.325324 -0.021831
0.338230 -0.021539
0.351150 -0.021237
0.364080 -0.020925
0.377036 -0.020598
0.390005 -0.020258
0.402987 -0.019906
0.415972 -0.019538
0.428961 -0.019156
0.441952 -0.018758
0.454937 -0.018348
0.467897 -0.017923
0.480825 -0.017482
0.493692 -0.017028
0.506538 -0.016554
0.519368 -0.016063
0.532213 -0.015546
0.545083 -0.015008
0.557963 -0.014439
0.570852 -0.013843
0.583740 -0.013208
0.596630 -0.012529
0.609518 -0.011803
0.622164 -0.011043
0.627483 -0.010705
0.630142 -0.010535
0.632642 -0.010648
0.637643 -0.010874
0.647983 -0.011310
0.660873 -0.011800
0.673760 -0.012228
0.686650 -0.012593
0.699539 -0.012892
0.712429 -0.013118
0.725313 -0.013274
0.738193 -0.013352
0.751071 -0.013351
0.763940 -0.013269
0.776802 -0.013108
0.789659 -0.012864
0.802513 -0.012545
0.815397 -0.012158
0.828289 -0.011705
0.841185 -0.011189
0.854082 -0.010633
0.866985 -0.010047
0.879894 -0.009430
0.892802 -0.008779
0.905712 -0.008095
0.918623 -0.007372
0.931529 -0.006611
0.944435 -0.005808
0.957338 -0.004959
0.970240 -0.004060
0.983139 -0.003108
0.996032 -0.002098
1.000000 -0.001799
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Similar airfoils
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Polars for HT05 (ht05-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ht05-il | 50,000 | 9 | 19.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 50,000 | 5 | 19.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 100,000 | 9 | 24.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 100,000 | 5 | 26.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 200,000 | 9 | 31.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 200,000 | 5 | 34.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 500,000 | 9 | 44.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 500,000 | 5 | 49.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 1,000,000 | 9 | 57.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 1,000,000 | 5 | 63.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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