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HT05 (ht05-il)

HT05 - Drela HT05 airfoil


Airfoil ht05-il
Details Dat file Parser  
(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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Lednicer format dat file
Selig format dat file

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Polars for HT05 (ht05-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ht05-il50,000919.2 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ht05-il50,000519.6 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ht05-il100,000924.8 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ht05-il100,000526.2 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ht05-il200,000931.1 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ht05-il200,000534.6 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ht05-il500,000944.4 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ht05-il500,000549.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ht05-il1,000,000957.7 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ht05-il1,000,000563.5 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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