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E210 (13.64%) (e210-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E210 (13.64%) (e210-il)
Reynolds number: 200,000
Max Cl/Cd: 79.58 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e210-il-200000-n5.txt
Download as CSV file: xf-e210-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E210  (13.64%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4058   0.08754   0.08416  -0.0478   1.0000   0.0182
  -9.750  -0.4254   0.08144   0.07813  -0.0491   1.0000   0.0180
  -9.500  -0.4930   0.05531   0.05180  -0.0734   0.9914   0.0171
  -9.250  -0.5112   0.04491   0.04091  -0.0885   0.9772   0.0170
  -9.000  -0.5069   0.03873   0.03417  -0.0942   0.9679   0.0173
  -8.750  -0.4925   0.03421   0.02908  -0.0974   0.9603   0.0178
  -8.500  -0.4761   0.03101   0.02536  -0.0984   0.9521   0.0184
  -8.250  -0.4503   0.02849   0.02244  -0.1003   0.9468   0.0192
  -8.000  -0.4281   0.02710   0.02097  -0.1006   0.9389   0.0200
  -7.750  -0.3988   0.02568   0.01936  -0.1020   0.9336   0.0209
  -7.500  -0.3748   0.02421   0.01767  -0.1021   0.9255   0.0216
  -7.250  -0.3451   0.02272   0.01595  -0.1031   0.9198   0.0224
  -7.000  -0.3194   0.02149   0.01453  -0.1031   0.9114   0.0232
  -6.750  -0.2883   0.02032   0.01319  -0.1041   0.9054   0.0243
  -6.500  -0.2604   0.01928   0.01211  -0.1047   0.8967   0.0256
  -6.250  -0.2259   0.01832   0.01107  -0.1063   0.8904   0.0269
  -6.000  -0.1944   0.01745   0.01011  -0.1073   0.8813   0.0280
  -5.750  -0.1553   0.01658   0.00910  -0.1098   0.8746   0.0294
  -5.500  -0.1200   0.01579   0.00822  -0.1117   0.8640   0.0314
  -5.250  -0.0821   0.01513   0.00750  -0.1140   0.8533   0.0345
  -5.000  -0.0430   0.01454   0.00676  -0.1164   0.8415   0.0378
  -4.750  -0.0056   0.01393   0.00608  -0.1185   0.8279   0.0438
  -4.500   0.0291   0.01343   0.00552  -0.1201   0.8128   0.0569
  -4.250   0.0612   0.01297   0.00508  -0.1212   0.7969   0.0842
  -4.000   0.0915   0.01259   0.00472  -0.1219   0.7808   0.1170
  -3.750   0.1206   0.01229   0.00444  -0.1224   0.7652   0.1537
  -3.500   0.1485   0.01191   0.00419  -0.1227   0.7501   0.2113
  -3.250   0.1754   0.01149   0.00399  -0.1229   0.7357   0.2947
  -3.000   0.2021   0.01122   0.00393  -0.1229   0.7223   0.3762
  -2.750   0.2291   0.01118   0.00390  -0.1227   0.7091   0.4247
  -2.500   0.2561   0.01120   0.00385  -0.1224   0.6967   0.4573
  -2.250   0.2832   0.01123   0.00382  -0.1221   0.6853   0.4837
  -2.000   0.3102   0.01129   0.00379  -0.1219   0.6746   0.5055
  -1.750   0.3371   0.01134   0.00376  -0.1216   0.6640   0.5231
  -1.500   0.3640   0.01138   0.00375  -0.1213   0.6542   0.5386
  -1.250   0.3910   0.01145   0.00373  -0.1211   0.6453   0.5529
  -1.000   0.4177   0.01149   0.00373  -0.1208   0.6360   0.5665
  -0.750   0.4446   0.01155   0.00374  -0.1205   0.6278   0.5800
  -0.500   0.4714   0.01161   0.00376  -0.1203   0.6194   0.5931
  -0.250   0.4984   0.01168   0.00378  -0.1201   0.6118   0.6057
   0.000   0.5250   0.01173   0.00381  -0.1198   0.6041   0.6178
   0.250   0.5517   0.01180   0.00386  -0.1195   0.5971   0.6302
   0.500   0.5783   0.01186   0.00391  -0.1192   0.5899   0.6427
   0.750   0.6050   0.01194   0.00396  -0.1190   0.5834   0.6550
   1.000   0.6316   0.01200   0.00404  -0.1187   0.5765   0.6677
   1.250   0.6581   0.01208   0.00411  -0.1184   0.5705   0.6808
   1.500   0.6843   0.01214   0.00421  -0.1181   0.5640   0.6948
   1.750   0.7103   0.01222   0.00431  -0.1177   0.5577   0.7105
   2.000   0.7362   0.01230   0.00442  -0.1173   0.5522   0.7281
   2.250   0.7615   0.01236   0.00455  -0.1167   0.5459   0.7473
   2.500   0.7864   0.01245   0.00467  -0.1160   0.5403   0.7700
   2.750   0.8105   0.01250   0.00482  -0.1152   0.5345   0.7969
   3.000   0.8339   0.01255   0.00495  -0.1142   0.5287   0.8295
   3.500   0.8852   0.01258   0.00516  -0.1129   0.5174   0.9560
   3.750   0.9135   0.01274   0.00529  -0.1132   0.5117   1.0000
   4.000   0.9403   0.01293   0.00546  -0.1131   0.5062   1.0000
   4.250   0.9666   0.01311   0.00567  -0.1130   0.5000   1.0000
   4.500   0.9929   0.01332   0.00585  -0.1128   0.4946   1.0000
   4.750   1.0188   0.01352   0.00607  -0.1126   0.4884   1.0000
   5.000   1.0444   0.01372   0.00628  -0.1123   0.4821   1.0000
   5.250   1.0699   0.01394   0.00652  -0.1119   0.4760   1.0000
   5.500   1.0946   0.01413   0.00676  -0.1115   0.4685   1.0000
   5.750   1.1191   0.01436   0.00697  -0.1109   0.4614   1.0000
   6.000   1.1430   0.01456   0.00724  -0.1103   0.4529   1.0000
   6.250   1.1668   0.01480   0.00749  -0.1096   0.4452   1.0000
   6.500   1.1900   0.01503   0.00776  -0.1089   0.4366   1.0000
   6.750   1.2128   0.01527   0.00805  -0.1081   0.4279   1.0000
   7.000   1.2348   0.01553   0.00833  -0.1071   0.4188   1.0000
   7.250   1.2565   0.01579   0.00866  -0.1061   0.4085   1.0000
   7.500   1.2774   0.01607   0.00898  -0.1049   0.3981   1.0000
   7.750   1.2971   0.01638   0.00931  -0.1036   0.3870   1.0000
   8.000   1.3160   0.01671   0.00968  -0.1021   0.3745   1.0000
   8.250   1.3341   0.01706   0.01007  -0.1005   0.3613   1.0000
   8.500   1.3497   0.01745   0.01048  -0.0984   0.3468   1.0000
   8.750   1.3636   0.01789   0.01093  -0.0961   0.3311   1.0000
   9.000   1.3760   0.01842   0.01144  -0.0936   0.3137   1.0000
   9.250   1.3873   0.01902   0.01204  -0.0910   0.2932   1.0000
   9.500   1.3953   0.01979   0.01275  -0.0880   0.2712   1.0000
   9.750   1.4019   0.02067   0.01356  -0.0850   0.2470   1.0000
  10.000   1.4061   0.02173   0.01454  -0.0817   0.2236   1.0000
  10.250   1.4089   0.02294   0.01566  -0.0786   0.2015   1.0000
  10.500   1.4115   0.02423   0.01690  -0.0756   0.1822   1.0000
  10.750   1.4141   0.02561   0.01825  -0.0728   0.1649   1.0000
  11.000   1.4160   0.02713   0.01976  -0.0702   0.1493   1.0000
  11.250   1.4174   0.02877   0.02139  -0.0677   0.1354   1.0000
  11.500   1.4185   0.03053   0.02316  -0.0656   0.1230   1.0000
  11.750   1.4189   0.03248   0.02512  -0.0636   0.1117   1.0000
  12.000   1.4182   0.03462   0.02727  -0.0619   0.1011   1.0000
  12.250   1.4167   0.03697   0.02963  -0.0603   0.0911   1.0000
  12.500   1.4162   0.03936   0.03205  -0.0591   0.0814   1.0000
  12.750   1.4144   0.04200   0.03470  -0.0581   0.0722   1.0000
  13.000   1.4118   0.04482   0.03754  -0.0573   0.0645   1.0000
  13.250   1.4098   0.04771   0.04046  -0.0567   0.0574   1.0000
  13.500   1.4088   0.05061   0.04343  -0.0563   0.0515   1.0000
  13.750   1.4059   0.05380   0.04665  -0.0561   0.0463   1.0000
  14.000   1.4058   0.05678   0.04973  -0.0560   0.0423   1.0000
  14.250   1.4035   0.06008   0.05309  -0.0560   0.0384   1.0000
  14.500   1.4015   0.06345   0.05655  -0.0562   0.0352   1.0000
  14.750   1.4003   0.06681   0.06001  -0.0565   0.0322   1.0000
  15.000   1.3963   0.07061   0.06387  -0.0570   0.0293   1.0000
  15.250   1.3945   0.07421   0.06758  -0.0575   0.0267   1.0000
  15.500   1.3911   0.07812   0.07158  -0.0583   0.0241   1.0000
  15.750   1.3861   0.08235   0.07589  -0.0592   0.0220   1.0000
  16.000   1.3831   0.08638   0.08003  -0.0601   0.0197   1.0000
  16.250   1.3777   0.09084   0.08458  -0.0614   0.0181   1.0000
  16.500   1.3728   0.09533   0.08918  -0.0627   0.0166   1.0000
  16.750   1.3685   0.09980   0.09379  -0.0641   0.0151   1.0000
  17.000   1.3625   0.10462   0.09870  -0.0658   0.0140   1.0000
  17.250   1.3560   0.10960   0.10378  -0.0677   0.0132   1.0000
  17.500   1.3512   0.11438   0.10870  -0.0695   0.0124   1.0000
  17.750   1.3460   0.11930   0.11375  -0.0716   0.0118   1.0000
  18.000   1.3405   0.12432   0.11890  -0.0738   0.0113   1.0000
  18.250   1.3345   0.12947   0.12416  -0.0762   0.0109   1.0000
  18.500   1.3276   0.13488   0.12968  -0.0789   0.0105   1.0000
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