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DU 06-W-200 VAWT airfoil (du06-w-200-dt) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: DU 06-W-200 VAWT airfoil (du06-w-200-dt)
Reynolds number: 50,000
Max Cl/Cd: 16.01 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-du06-w-200-dt-50000-n5.txt
Download as CSV file: xf-du06-w-200-dt-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.7344   0.12330   0.11532   0.0000   1.0000   0.1418
 -14.750  -0.7105   0.12436   0.11634   0.0014   1.0000   0.1451
 -14.500  -0.8662   0.09024   0.08208  -0.0168   1.0000   0.1559
 -14.250  -0.7764   0.10253   0.09448  -0.0092   1.0000   0.1590
 -14.000  -0.8546   0.08526   0.07704  -0.0177   1.0000   0.1661
 -13.750  -0.9394   0.07029   0.06164  -0.0241   1.0000   0.1700
 -13.500  -0.9010   0.07216   0.06368  -0.0223   1.0000   0.1762
 -13.250  -0.9216   0.06662   0.05796  -0.0238   1.0000   0.1817
 -13.000  -0.9469   0.06090   0.05197  -0.0251   1.0000   0.1867
 -12.750  -0.9222   0.06083   0.05202  -0.0243   1.0000   0.1934
 -12.500  -0.9366   0.05662   0.04759  -0.0248   1.0000   0.1997
 -12.250  -0.9234   0.05524   0.04624  -0.0244   1.0000   0.2064
 -12.000  -0.9211   0.05287   0.04378  -0.0242   1.0000   0.2136
 -11.750  -0.9166   0.05070   0.04154  -0.0239   1.0000   0.2210
 -11.500  -0.9057   0.04922   0.04003  -0.0235   1.0000   0.2289
 -11.250  -0.9003   0.04719   0.03792  -0.0231   1.0000   0.2369
 -11.000  -0.8876   0.04592   0.03664  -0.0226   1.0000   0.2457
 -10.750  -0.8772   0.04440   0.03510  -0.0221   1.0000   0.2546
 -10.500  -0.8669   0.04292   0.03358  -0.0215   1.0000   0.2640
 -10.250  -0.8503   0.04198   0.03268  -0.0209   1.0000   0.2736
 -10.000  -0.8467   0.04010   0.03069  -0.0202   1.0000   0.2842
  -9.750  -0.8235   0.03969   0.03039  -0.0196   1.0000   0.2943
  -9.500  -0.8103   0.03860   0.02933  -0.0188   1.0000   0.3052
  -9.250  -0.8033   0.03721   0.02788  -0.0179   1.0000   0.3170
  -9.000  -0.7807   0.03688   0.02767  -0.0172   1.0000   0.3282
  -8.750  -0.7658   0.03614   0.02698  -0.0162   1.0000   0.3403
  -8.500  -0.7554   0.03515   0.02602  -0.0152   1.0000   0.3531
  -8.250  -0.7405   0.03455   0.02548  -0.0142   1.0000   0.3660
  -8.000  -0.7220   0.03435   0.02539  -0.0130   1.0000   0.3783
  -7.750  -0.7132   0.03394   0.02508  -0.0111   1.0000   0.3905
  -7.500  -0.6993   0.03347   0.02463  -0.0105   0.9877   0.4045
  -7.250  -0.6562   0.03335   0.02450  -0.0136   0.9649   0.4215
  -7.000  -0.6164   0.03326   0.02436  -0.0159   0.9422   0.4377
  -6.750  -0.5789   0.03320   0.02424  -0.0176   0.9207   0.4537
  -6.500  -0.5347   0.03405   0.02506  -0.0185   0.9018   0.4649
  -6.250  -0.4998   0.03450   0.02543  -0.0186   0.8827   0.4767
  -6.000  -0.4742   0.03450   0.02531  -0.0181   0.8640   0.4899
  -5.750  -0.4450   0.03507   0.02578  -0.0170   0.8465   0.5001
  -5.500  -0.4177   0.03560   0.02621  -0.0158   0.8301   0.5094
  -5.250  -0.3987   0.03545   0.02595  -0.0146   0.8144   0.5224
  -5.000  -0.3674   0.03645   0.02685  -0.0131   0.8000   0.5285
  -4.750  -0.3477   0.03641   0.02669  -0.0120   0.7867   0.5403
  -4.500  -0.3210   0.03698   0.02713  -0.0105   0.7747   0.5483
  -4.250  -0.2986   0.03711   0.02719  -0.0096   0.7617   0.5585
  -4.000  -0.2811   0.03687   0.02684  -0.0087   0.7502   0.5714
  -3.750  -0.2519   0.03747   0.02733  -0.0074   0.7401   0.5778
  -3.500  -0.2329   0.03732   0.02711  -0.0068   0.7287   0.5896
  -3.250  -0.2163   0.03700   0.02668  -0.0059   0.7198   0.6029
  -3.000  -0.1869   0.03751   0.02714  -0.0051   0.7094   0.6087
  -2.750  -0.1693   0.03725   0.02679  -0.0043   0.7008   0.6209
  -2.500  -0.1434   0.03748   0.02697  -0.0036   0.6914   0.6285
  -2.250  -0.1236   0.03734   0.02675  -0.0028   0.6834   0.6390
  -2.000  -0.1081   0.03702   0.02638  -0.0022   0.6747   0.6520
  -1.750  -0.0785   0.03729   0.02658  -0.0014   0.6674   0.6570
  -1.500  -0.0626   0.03703   0.02628  -0.0009   0.6585   0.6693
  -1.250  -0.0338   0.03716   0.02635   0.0000   0.6522   0.6745
  -1.000  -0.0182   0.03698   0.02615   0.0004   0.6434   0.6863
  -0.750   0.0097   0.03706   0.02619   0.0012   0.6365   0.6915
  -0.500   0.0258   0.03686   0.02595   0.0018   0.6291   0.7027
  -0.250   0.0523   0.03696   0.02605   0.0025   0.6215   0.7078
   0.000   0.0745   0.03677   0.02578   0.0033   0.6157   0.7162
   0.250   0.0942   0.03685   0.02591   0.0039   0.6071   0.7236
   0.500   0.1184   0.03672   0.02572   0.0047   0.6010   0.7306
   0.750   0.1359   0.03671   0.02571   0.0054   0.5932   0.7390
   1.000   0.1601   0.03671   0.02571   0.0061   0.5862   0.7448
   1.250   0.1792   0.03644   0.02536   0.0068   0.5808   0.7539
   1.500   0.2006   0.03669   0.02570   0.0076   0.5719   0.7588
   1.750   0.2243   0.03650   0.02546   0.0083   0.5661   0.7655
   2.000   0.2411   0.03664   0.02564   0.0091   0.5579   0.7725
   2.250   0.2647   0.03660   0.02562   0.0098   0.5509   0.7778
   2.500   0.2862   0.03650   0.02547   0.0105   0.5449   0.7847
   2.750   0.3035   0.03674   0.02579   0.0113   0.5360   0.7904
   3.000   0.3299   0.03650   0.02551   0.0120   0.5306   0.7956
   3.250   0.3438   0.03692   0.02601   0.0128   0.5214   0.8022
   3.500   0.3680   0.03677   0.02585   0.0134   0.5149   0.8070
   3.750   0.3871   0.03702   0.02617   0.0143   0.5069   0.8120
   4.000   0.4069   0.03713   0.02630   0.0149   0.4991   0.8177
   4.250   0.4323   0.03694   0.02608   0.0153   0.4931   0.8225
   4.500   0.4458   0.03754   0.02681   0.0164   0.4833   0.8271
   4.750   0.4744   0.03717   0.02639   0.0167   0.4778   0.8319
   5.000   0.4836   0.03806   0.02741   0.0175   0.4673   0.8373
   5.250   0.5114   0.03775   0.02710   0.0180   0.4614   0.8410
   5.500   0.5214   0.03861   0.02810   0.0191   0.4512   0.8456
   5.750   0.5486   0.03839   0.02787   0.0193   0.4447   0.8499
   6.000   0.5590   0.03935   0.02896   0.0199   0.4349   0.8545
   6.250   0.5848   0.03919   0.02882   0.0204   0.4280   0.8579
   6.500   0.5943   0.04018   0.02994   0.0212   0.4183   0.8622
   6.750   0.6198   0.04015   0.02993   0.0214   0.4112   0.8660
   7.000   0.6286   0.04139   0.03129   0.0217   0.4014   0.8700
   7.250   0.6539   0.04124   0.03118   0.0221   0.3943   0.8732
   7.500   0.6572   0.04280   0.03287   0.0228   0.3843   0.8772
   7.750   0.6837   0.04270   0.03281   0.0229   0.3776   0.8809
   8.000   0.6804   0.04489   0.03513   0.0233   0.3673   0.8851
   8.250   0.7094   0.04457   0.03484   0.0234   0.3610   0.8880
   8.500   0.6948   0.04794   0.03837   0.0234   0.3501   0.8923
   8.750   0.7261   0.04733   0.03779   0.0237   0.3445   0.8961
   9.000   0.7087   0.05195   0.04255   0.0220   0.3327   0.9009
   9.250   0.7435   0.05080   0.04144   0.0227   0.3280   0.9046
   9.750   0.7533   0.05551   0.04633   0.0211   0.3115   0.9130
  10.250   0.7565   0.06140   0.05242   0.0188   0.2950   0.9225
  10.500   0.8051   0.05838   0.04941   0.0204   0.2928   0.9285
  10.750   0.7512   0.06881   0.06002   0.0159   0.2785   0.9347
  11.000   0.7982   0.06574   0.05699   0.0174   0.2765   0.9431
  11.250   0.7414   0.07747   0.06887   0.0121   0.2621   0.9509
  11.750   0.7240   0.08737   0.07893   0.0074   0.2460   1.0000
  12.250   0.7083   0.09864   0.09031   0.0016   0.2309   1.0000
  12.500   0.7228   0.10075   0.09248   0.0004   0.2267   1.0000
  13.000   0.7197   0.11018   0.10202  -0.0046   0.2138   1.0000
  13.500   0.6995   0.12283   0.11477  -0.0114   0.2008   1.0000
  13.750   0.7242   0.12326   0.11525  -0.0118   0.1977   1.0000
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