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HT08 (ht08-il)

HT08 - Drela HT08 airfoil


Airfoil ht08-il
Details Dat file Parser  
(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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Polars for HT08 (ht08-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ht08-il50,000921.6 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   ht08-il50,000520.1 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ht08-il100,000928.8 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ht08-il100,000526.1 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ht08-il200,000933.1 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   ht08-il200,000534.2 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ht08-il500,000944.1 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ht08-il500,000548.9 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ht08-il1,000,000956.7 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ht08-il1,000,000563.5 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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