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E180 (8.59%) (e180-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E180 (8.59%) (e180-il)
Reynolds number: 100,000
Max Cl/Cd: 52.71 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e180-il-100000.txt
Download as CSV file: xf-e180-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E180  (8.59%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4969   0.09927   0.09481  -0.0002   1.0000   0.0876
  -8.250  -0.5040   0.09605   0.09169  -0.0052   1.0000   0.0902
  -8.000  -0.5188   0.09270   0.08845  -0.0133   1.0000   0.0910
  -7.750  -0.4906   0.08815   0.08388  -0.0062   1.0000   0.0972
  -7.500  -0.4094   0.07415   0.07023  -0.0112   1.0000   0.1102
  -7.250  -0.4115   0.07023   0.06638  -0.0133   1.0000   0.1147
  -7.000  -0.4363   0.06540   0.06158  -0.0238   1.0000   0.1184
  -6.750  -0.4232   0.06046   0.05672  -0.0219   1.0000   0.1216
  -6.500  -0.4132   0.05659   0.05288  -0.0224   1.0000   0.1274
  -6.250  -0.4600   0.06395   0.05980  -0.0254   1.0000   0.1277
  -6.000  -0.4501   0.05953   0.05531  -0.0289   1.0000   0.1363
  -5.750  -0.4386   0.05578   0.05141  -0.0319   1.0000   0.1485
  -5.500  -0.4275   0.05284   0.04836  -0.0330   1.0000   0.1618
  -5.250  -0.4213   0.05014   0.04583  -0.0304   1.0000   0.1652
  -5.000  -0.4328   0.04894   0.04449  -0.0276   1.0000   0.1764
  -4.750  -0.4027   0.03520   0.02885  -0.0304   0.9961   0.0633
  -4.500  -0.3648   0.02998   0.02309  -0.0334   0.9871   0.0565
  -4.250  -0.3222   0.02636   0.01841  -0.0354   0.9785   0.0523
  -4.000  -0.2799   0.02347   0.01523  -0.0386   0.9712   0.0558
  -3.750  -0.2378   0.02165   0.01305  -0.0411   0.9627   0.0624
  -3.500  -0.1932   0.01937   0.01068  -0.0439   0.9566   0.0708
  -3.250  -0.1579   0.01783   0.00923  -0.0452   0.9464   0.0999
  -3.000  -0.1264   0.01625   0.00810  -0.0461   0.9364   0.1873
  -2.750  -0.1008   0.01426   0.00753  -0.0461   0.9271   0.4431
  -2.500  -0.0407   0.01277   0.00744  -0.0490   0.9252   0.9046
  -2.250   0.0626   0.01250   0.00661  -0.0629   0.9270   1.0000
  -2.000   0.0881   0.01258   0.00640  -0.0628   0.9128   1.0000
  -1.750   0.1118   0.01272   0.00630  -0.0623   0.9001   1.0000
  -1.500   0.1337   0.01289   0.00627  -0.0614   0.8880   1.0000
  -1.250   0.1551   0.01310   0.00630  -0.0603   0.8762   1.0000
  -1.000   0.1769   0.01332   0.00635  -0.0594   0.8654   1.0000
  -0.750   0.1986   0.01355   0.00643  -0.0582   0.8556   1.0000
  -0.500   0.2204   0.01378   0.00652  -0.0570   0.8464   1.0000
  -0.250   0.2431   0.01406   0.00669  -0.0563   0.8364   1.0000
   0.000   0.2655   0.01432   0.00685  -0.0552   0.8278   1.0000
   0.250   0.2882   0.01458   0.00701  -0.0542   0.8192   1.0000
   0.500   0.3115   0.01489   0.00726  -0.0536   0.8100   1.0000
   0.750   0.3340   0.01514   0.00742  -0.0523   0.8028   1.0000
   1.000   0.3577   0.01548   0.00774  -0.0518   0.7933   1.0000
   1.250   0.3811   0.01580   0.00803  -0.0510   0.7852   1.0000
   1.500   0.4043   0.01608   0.00827  -0.0500   0.7772   1.0000
   1.750   0.4280   0.01646   0.00866  -0.0495   0.7680   1.0000
   2.000   0.4510   0.01667   0.00883  -0.0480   0.7612   1.0000
   2.250   0.4748   0.01706   0.00928  -0.0476   0.7509   1.0000
   2.500   0.4982   0.01739   0.00964  -0.0467   0.7418   1.0000
   2.750   0.5216   0.01756   0.00980  -0.0453   0.7337   1.0000
   3.000   0.5451   0.01790   0.01020  -0.0446   0.7228   1.0000
   3.250   0.5685   0.01817   0.01052  -0.0435   0.7122   1.0000
   3.500   0.5920   0.01827   0.01069  -0.0420   0.7025   1.0000
   3.750   0.6156   0.01835   0.01081  -0.0406   0.6917   1.0000
   4.000   0.6391   0.01850   0.01105  -0.0394   0.6792   1.0000
   4.250   0.6627   0.01856   0.01119  -0.0380   0.6663   1.0000
   4.500   0.6865   0.01853   0.01128  -0.0365   0.6527   1.0000
   4.750   0.7104   0.01840   0.01123  -0.0349   0.6383   1.0000
   5.000   0.7345   0.01818   0.01109  -0.0331   0.6229   1.0000
   5.250   0.7590   0.01787   0.01085  -0.0313   0.6067   1.0000
   5.500   0.7827   0.01766   0.01084  -0.0298   0.5855   1.0000
   5.750   0.8071   0.01719   0.01042  -0.0279   0.5636   1.0000
   6.000   0.8300   0.01666   0.01002  -0.0259   0.5282   1.0000
   6.250   0.8513   0.01615   0.00947  -0.0237   0.4693   1.0000
   6.500   0.8685   0.01648   0.00936  -0.0215   0.3585   1.0000
   6.750   0.8783   0.01840   0.01042  -0.0195   0.2169   1.0000
   7.000   0.8801   0.02181   0.01276  -0.0170   0.0994   1.0000
   7.250   0.8919   0.02392   0.01467  -0.0148   0.0752   1.0000
   7.500   0.9078   0.02561   0.01632  -0.0132   0.0644   1.0000
   7.750   0.9256   0.02778   0.01829  -0.0118   0.0586   1.0000
   8.000   0.9494   0.02960   0.02030  -0.0106   0.0555   1.0000
   8.250   0.9742   0.03184   0.02270  -0.0097   0.0531   1.0000
   8.500   0.9984   0.03442   0.02555  -0.0087   0.0516   1.0000
   8.750   1.0190   0.03697   0.02826  -0.0079   0.0491   1.0000
   9.000   1.0365   0.04148   0.03295  -0.0073   0.0469   1.0000
   9.250   1.0507   0.04494   0.03686  -0.0060   0.0468   1.0000
   9.500   1.0625   0.04925   0.04159  -0.0047   0.0471   1.0000
   9.750   1.0724   0.05162   0.04445  -0.0028   0.0480   1.0000
  10.000   1.0599   0.05613   0.04984   0.0001   0.0509   1.0000
  10.250   1.0464   0.06121   0.05539   0.0019   0.0533   1.0000
  10.500   1.0331   0.06573   0.06017   0.0032   0.0551   1.0000
  10.750   1.0184   0.06995   0.06454   0.0043   0.0563   1.0000
  11.000   1.0165   0.07481   0.06955   0.0046   0.0602   1.0000
  11.250   0.9822   0.07932   0.07428   0.0032   0.0608   1.0000
  11.500   0.9483   0.08556   0.08069  -0.0007   0.0612   1.0000
  11.750   0.9125   0.09401   0.08925  -0.0071   0.0618   1.0000
  12.000   0.7986   0.09336   0.08884  -0.0042   0.0569   1.0000
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