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DU 06-W-200 VAWT airfoil (du06-w-200-dt)

DU 06-W-200 VAWT airfoil - DU 06-W-200 airfoil for Small Vertical Axis Wind Turbines (VAWT)


Airfoil du06-w-200-dt
Details Dat file Parser  
(du06-w-200-dt) DU 06-W-200 VAWT airfoil
DU 06-W-200 airfoil for Small Vertical Axis Wind Turbines (VAWT)
Max thickness 19.8% at 31.1% chord.
Max camber 0.5% at 84.6% chord
Source TU Delft
Source dat file
The dat file is in Selig format
DU 06-W-200  VAWT airfoil
1.000030  0.000330
0.995071  0.000991
0.988745  0.001790
0.980844  0.002821
0.971354  0.004134
0.960703  0.005676
0.949361  0.007380
0.937673  0.009188
0.925781  0.011064
0.913799  0.012967
0.901782  0.014892
0.889754  0.016828
0.877727  0.018779
0.865704  0.020741
0.853697  0.022719
0.841679  0.024714
0.829686  0.026717
0.817740  0.028741
0.805771  0.030796
0.793799  0.032857
0.781854  0.034939
0.769889  0.037053
0.757924  0.039180
0.746007  0.041327
0.734077  0.043511
0.722128  0.045716
0.710225  0.047936
0.698325  0.050176
0.686453  0.052417
0.674589  0.054685
0.662687  0.056949
0.650773  0.059221
0.638859  0.061480
0.626934  0.063716
0.615006  0.065934
0.603147  0.068109
0.591292  0.070229
0.579430  0.072307
0.567547  0.074343
0.555676  0.076339
0.543792  0.078282
0.531879  0.080195
0.519984  0.082060
0.508056  0.083885
0.496115  0.085679
0.484187  0.087431
0.472242  0.089147
0.460354  0.090814
0.448446  0.092426
0.436599  0.093990
0.424787  0.095466
0.413003  0.096877
0.401290  0.098182
0.389595  0.099392
0.377963  0.100483
0.366361  0.101453
0.354814  0.102282
0.343266  0.102969
0.331726  0.103514
0.320178  0.103912
0.308593  0.104180
0.297054  0.104309
0.285489  0.104290
0.273928  0.104142
0.262419  0.103851
0.250920  0.103406
0.239441  0.102815
0.228016  0.102074
0.216637  0.101172
0.205318  0.100103
0.194052  0.098861
0.182866  0.097447
0.171792  0.095845
0.160792  0.094042
0.149938  0.092038
0.139170  0.089806
0.128563  0.087366
0.118128  0.084689
0.107876  0.081772
0.097863  0.078610
0.088085  0.075175
0.078586  0.071484
0.069402  0.067515
0.060586  0.063284
0.052175  0.058794
0.044254  0.054063
0.036871  0.049124
0.030107  0.044037
0.024057  0.038898
0.018781  0.033816
0.014332  0.028930
0.010681  0.024359
0.007756  0.020195
0.005460  0.016479
0.003720  0.013151
0.002419  0.010168
0.001446  0.007489
0.000702  0.005102
0.000259  0.002932
0.000038  0.000944
0.000046  -0.000911
0.000385  -0.002855
0.000980  -0.004968
0.001862  -0.007256
0.003065  -0.009755
0.004630  -0.012507
0.006653  -0.015533
0.009224  -0.018871
0.012477  -0.022518
0.016534  -0.026484
0.021456  -0.030740
0.027288  -0.035182
0.033970  -0.039704
0.041417  -0.044177
0.049507  -0.048508
0.058159  -0.052655
0.067244  -0.056572
0.076717  -0.060244
0.086510  -0.063669
0.096591  -0.066865
0.106888  -0.069816
0.117402  -0.072555
0.128085  -0.075067
0.138941  -0.077391
0.149918  -0.079520
0.161017  -0.081472
0.172199  -0.083251
0.183459  -0.084857
0.194835  -0.086310
0.206246  -0.087627
0.217718  -0.088783
0.229267  -0.089822
0.240824  -0.090722
0.252445  -0.091498
0.264104  -0.092160
0.275771  -0.092709
0.287455  -0.093136
0.299179  -0.093459
0.310901  -0.093673
0.322646  -0.093783
0.334386  -0.093785
0.346164  -0.093688
0.357917  -0.093494
0.369702  -0.093194
0.381483  -0.092805
0.393277  -0.092315
0.405087  -0.091739
0.416892  -0.091073
0.428714  -0.090318
0.440534  -0.089484
0.452348  -0.088562
0.464176  -0.087561
0.475993  -0.086480
0.487811  -0.085322
0.499605  -0.084091
0.511354  -0.082780
0.523068  -0.081386
0.534692  -0.079904
0.546245  -0.078317
0.557686  -0.076620
0.569025  -0.074781
0.580320  -0.072781
0.591592  -0.070620
0.602880  -0.068293
0.614212  -0.065812
0.625585  -0.063191
0.637030  -0.060434
0.648597  -0.057558
0.660268  -0.054610
0.671981  -0.051627
0.683701  -0.048657
0.695430  -0.045719
0.707153  -0.042807
0.718795  -0.039964
0.730458  -0.037180
0.742078  -0.034463
0.753726  -0.031815
0.765344  -0.029234
0.776960  -0.026740
0.788585  -0.024315
0.800182  -0.021981
0.811752  -0.019742
0.823301  -0.017617
0.834860  -0.015593
0.846387  -0.013685
0.857897  -0.011903
0.869394  -0.010249
0.880860  -0.008731
0.892291  -0.007367
0.903719  -0.006160
0.915150  -0.005108
0.926586  -0.004214
0.938030  -0.003470
0.949424  -0.002872
0.960662  -0.002393
0.971321  -0.001989
0.980723  -0.001708
0.988627  -0.001544
0.994978  -0.001364
0.999970  -0.001169

Dat file parser warnings
  • Line 2 - X value too large but included: 1.000030 0.000330
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Polars for DU 06-W-200 VAWT airfoil (du06-w-200-dt)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   du06-w-200-dt50,000911 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   du06-w-200-dt50,000516 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   du06-w-200-dt100,000932.7 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   du06-w-200-dt100,000536.1 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   du06-w-200-dt200,000948.6 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   du06-w-200-dt200,000551.1 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   du06-w-200-dt500,000971.5 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   du06-w-200-dt500,000571.2 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   du06-w-200-dt1,000,000990.2 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   du06-w-200-dt1,000,000587.4 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
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