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DU 06-W-200 VAWT airfoil (du06-w-200-dt) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: DU 06-W-200 VAWT airfoil (du06-w-200-dt)
Reynolds number: 50,000
Max Cl/Cd: 11.05 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-du06-w-200-dt-50000.txt
Download as CSV file: xf-du06-w-200-dt-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DU 06-W-200  VAWT airfoil                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4452   0.13315   0.12505   0.0216   1.0000   0.4368
 -11.250  -0.4139   0.12879   0.12063   0.0206   1.0000   0.4487
 -11.000  -0.4854   0.11676   0.10857   0.0121   1.0000   0.3663
 -10.750  -0.4805   0.11194   0.10371   0.0104   1.0000   0.3638
 -10.500  -0.4849   0.10695   0.09870   0.0085   1.0000   0.3632
 -10.250  -0.4932   0.10166   0.09339   0.0066   1.0000   0.3637
 -10.000  -0.5142   0.09539   0.08713   0.0042   1.0000   0.3663
  -9.750  -0.4836   0.09463   0.08632   0.0050   1.0000   0.3775
  -9.500  -0.5032   0.08871   0.08041   0.0029   1.0000   0.3823
  -9.250  -0.4817   0.08709   0.07875   0.0031   1.0000   0.3920
  -9.000  -0.5055   0.08116   0.07284   0.0014   1.0000   0.4003
  -8.750  -0.4709   0.08096   0.07261   0.0021   1.0000   0.4110
  -8.500  -0.4917   0.07555   0.06723   0.0007   1.0000   0.4210
  -8.250  -0.4683   0.07455   0.06621   0.0010   1.0000   0.4327
  -8.000  -0.4448   0.07337   0.06502   0.0010   1.0000   0.4438
  -7.750  -0.4495   0.06994   0.06161   0.0005   1.0000   0.4560
  -7.500  -0.4496   0.06717   0.05888   0.0002   1.0000   0.4692
  -7.250  -0.4058   0.06775   0.05943   0.0002   1.0000   0.4807
  -7.000  -0.3905   0.06633   0.05805  -0.0001   1.0000   0.4935
  -6.750  -0.3969   0.06419   0.05599   0.0003   1.0000   0.5064
  -6.500  -0.3947   0.06428   0.05616   0.0027   1.0000   0.5164
  -6.250  -0.4847   0.06263   0.05472   0.0123   1.0000   0.5221
  -6.000  -0.4696   0.06398   0.05609   0.0148   1.0000   0.5311
  -5.750  -0.4327   0.06368   0.05571   0.0115   0.9917   0.5465
  -5.500  -0.3703   0.06288   0.05475   0.0042   0.9780   0.5661
  -5.250  -0.3256   0.06148   0.05322  -0.0021   0.9640   0.5860
  -5.000  -0.2416   0.06109   0.05269  -0.0104   0.9520   0.6049
  -4.750  -0.1728   0.06017   0.05164  -0.0175   0.9392   0.6234
  -4.500  -0.1172   0.05919   0.05056  -0.0228   0.9257   0.6420
  -4.250  -0.0722   0.05821   0.04949  -0.0266   0.9118   0.6601
  -4.000  -0.0335   0.05735   0.04855  -0.0290   0.8983   0.6784
  -3.750  -0.0065   0.05674   0.04787  -0.0298   0.8835   0.6948
  -3.500   0.0194   0.05621   0.04730  -0.0302   0.8699   0.7122
  -3.250   0.0453   0.05563   0.04665  -0.0306   0.8577   0.7295
  -3.000   0.0713   0.05503   0.04599  -0.0307   0.8463   0.7482
  -2.750   0.0939   0.05461   0.04555  -0.0310   0.8342   0.7659
  -2.500   0.1175   0.05408   0.04497  -0.0311   0.8238   0.7839
  -2.250   0.1404   0.05356   0.04442  -0.0312   0.8131   0.8018
  -2.000   0.1641   0.05313   0.04397  -0.0319   0.8026   0.8186
  -1.750   0.2013   0.05207   0.04288  -0.0333   0.7931   0.8414
  -1.500   0.2156   0.05202   0.04282  -0.0336   0.7824   0.8512
  -1.250   0.2439   0.05124   0.04199  -0.0343   0.7738   0.8670
  -1.000   0.2702   0.05085   0.04162  -0.0362   0.7625   0.8797
  -0.750   0.2906   0.05052   0.04126  -0.0365   0.7538   0.8905
  -0.500   0.3082   0.05045   0.04120  -0.0369   0.7438   0.8981
  -0.250   0.3310   0.05028   0.04103  -0.0381   0.7342   0.9080
   0.000   0.3471   0.05026   0.04100  -0.0378   0.7250   0.9150
   0.250   0.3664   0.05044   0.04121  -0.0388   0.7146   0.9227
   0.500   0.3889   0.05017   0.04091  -0.0390   0.7060   0.9306
   0.750   0.3984   0.05100   0.04179  -0.0391   0.6951   0.9361
   1.000   0.4339   0.05017   0.04092  -0.0403   0.6868   0.9455
   1.250   0.4318   0.05178   0.04261  -0.0395   0.6755   0.9493
   1.500   0.4664   0.05159   0.04243  -0.0420   0.6650   0.9577
   1.750   0.4800   0.05217   0.04304  -0.0416   0.6550   0.9634
   2.000   0.4971   0.05317   0.04410  -0.0429   0.6436   0.9692
   2.250   0.5354   0.05229   0.04320  -0.0441   0.6348   0.9771
   2.500   0.5372   0.05446   0.04547  -0.0445   0.6222   0.9813
   2.750   0.5606   0.05522   0.04627  -0.0460   0.6112   0.9874
   3.000   0.5968   0.05492   0.04600  -0.0477   0.6010   0.9940
   3.250   0.5940   0.05769   0.04887  -0.0479   0.5887   0.9978
   3.500   0.6279   0.05684   0.04799  -0.0476   0.5806   1.0000
   3.750   0.5969   0.06081   0.05205  -0.0448   0.5691   1.0000
   4.000   0.5910   0.06265   0.05390  -0.0422   0.5605   1.0000
   4.250   0.5648   0.06557   0.05684  -0.0386   0.5515   1.0000
   4.500   0.5546   0.06742   0.05871  -0.0355   0.5435   1.0000
   4.750   0.4863   0.07139   0.06266  -0.0280   0.5386   1.0000
   5.000   0.5390   0.07053   0.06181  -0.0292   0.5285   1.0000
   5.250   0.4620   0.07487   0.06613  -0.0218   0.5253   1.0000
   5.500   0.4277   0.07748   0.06875  -0.0178   0.5212   1.0000
   5.750   0.4628   0.07743   0.06870  -0.0173   0.5110   1.0000
   6.000   0.4199   0.08052   0.07179  -0.0133   0.5094   1.0000
   6.250   0.3908   0.08303   0.07430  -0.0101   0.5083   1.0000
   6.500   0.3703   0.08531   0.07659  -0.0076   0.5084   1.0000
   6.750   0.3637   0.08761   0.07890  -0.0060   0.5107   1.0000
   7.000   0.2715   0.09554   0.08692  -0.0059   0.5990   1.0000
   7.250   0.2386   0.09452   0.08589  -0.0010   0.5884   1.0000
   7.500   0.2538   0.09682   0.08819  -0.0006   0.5804   1.0000
   7.750   0.2491   0.09734   0.08871   0.0012   0.5679   1.0000
   8.000   0.2551   0.09952   0.09091   0.0010   0.5612   1.0000
   8.250   0.2752   0.10184   0.09326  -0.0001   0.5486   1.0000
   8.500   0.2711   0.10323   0.09468   0.0000   0.5380   1.0000
   8.750   0.3150   0.10802   0.09951  -0.0033   0.5293   1.0000
   9.000   0.2971   0.10823   0.09975  -0.0028   0.5189   1.0000
   9.250   0.3354   0.11301   0.10458  -0.0058   0.5115   1.0000
   9.500   0.3271   0.11368   0.10527  -0.0060   0.4994   1.0000
   9.750   0.3504   0.11767   0.10932  -0.0083   0.4929   1.0000
  10.000   0.3522   0.11930   0.11099  -0.0093   0.4823   1.0000
  10.250   0.3834   0.12415   0.11589  -0.0121   0.4763   1.0000
  10.500   0.3784   0.12512   0.11689  -0.0128   0.4648   1.0000
  10.750   0.4088   0.13008   0.12192  -0.0155   0.4589   1.0000
  11.000   0.4005   0.13102   0.12289  -0.0164   0.4494   1.0000
  11.250   0.4423   0.13694   0.12888  -0.0193   0.4428   1.0000
  11.500   0.4245   0.13714   0.12909  -0.0202   0.4341   1.0000
  11.750   0.4612   0.14238   0.13440  -0.0226   0.4261   1.0000
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