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)
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(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
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for DU 06-W-200 VAWT airfoil (du06-w-200-dt)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| du06-w-200-dt | 50,000 | 9 | 11 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du06-w-200-dt | 50,000 | 5 | 16 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du06-w-200-dt | 100,000 | 9 | 32.7 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du06-w-200-dt | 100,000 | 5 | 36.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du06-w-200-dt | 200,000 | 9 | 48.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du06-w-200-dt | 200,000 | 5 | 51.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du06-w-200-dt | 500,000 | 9 | 71.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du06-w-200-dt | 500,000 | 5 | 71.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du06-w-200-dt | 1,000,000 | 9 | 90.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du06-w-200-dt | 1,000,000 | 5 | 87.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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