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E186 (10.27%) (e186-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E186 (10.27%) (e186-il)
Reynolds number: 500,000
Max Cl/Cd: 71.14 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e186-il-500000-n5.txt
Download as CSV file: xf-e186-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E186  (10.27%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.7399   0.08447   0.08264   0.0207   1.0000   0.0077
 -10.000  -0.8510   0.05459   0.05251   0.0018   1.0000   0.0071
  -9.750  -0.8878   0.04824   0.04587   0.0047   1.0000   0.0071
  -9.500  -0.9010   0.04343   0.04076   0.0069   1.0000   0.0072
  -9.250  -0.9069   0.03895   0.03592   0.0092   1.0000   0.0073
  -9.000  -0.9071   0.03612   0.03266   0.0124   0.8781   0.0076
  -8.750  -0.9035   0.03326   0.02935   0.0154   0.8404   0.0078
  -8.500  -0.8944   0.03063   0.02628   0.0177   0.8130   0.0081
  -8.250  -0.8813   0.02833   0.02357   0.0196   0.7903   0.0084
  -8.000  -0.8643   0.02657   0.02146   0.0211   0.7705   0.0088
  -7.750  -0.8442   0.02537   0.01998   0.0223   0.7528   0.0093
  -7.500  -0.8228   0.02437   0.01871   0.0233   0.7372   0.0096
  -7.250  -0.8007   0.02345   0.01754   0.0242   0.7229   0.0098
  -7.000  -0.7810   0.02148   0.01522   0.0254   0.7106   0.0101
  -6.750  -0.7607   0.01956   0.01302   0.0266   0.6994   0.0105
  -6.500  -0.7380   0.01842   0.01170   0.0275   0.6888   0.0108
  -6.250  -0.7143   0.01752   0.01066   0.0282   0.6783   0.0111
  -6.000  -0.6902   0.01672   0.00973   0.0288   0.6689   0.0114
  -5.750  -0.6657   0.01607   0.00897   0.0295   0.6604   0.0118
  -5.500  -0.6408   0.01549   0.00829   0.0300   0.6516   0.0123
  -5.250  -0.6160   0.01489   0.00757   0.0306   0.6440   0.0128
  -5.000  -0.5913   0.01427   0.00684   0.0313   0.6364   0.0131
  -4.750  -0.5664   0.01371   0.00618   0.0319   0.6297   0.0135
  -4.500  -0.5412   0.01322   0.00558   0.0325   0.6226   0.0139
  -4.250  -0.5156   0.01280   0.00507   0.0330   0.6164   0.0143
  -4.000  -0.4897   0.01243   0.00461   0.0335   0.6100   0.0148
  -3.750  -0.4635   0.01212   0.00420   0.0339   0.6042   0.0151
  -3.500  -0.4371   0.01181   0.00382   0.0343   0.5981   0.0155
  -3.250  -0.4108   0.01151   0.00343   0.0346   0.5925   0.0163
  -3.000  -0.3841   0.01126   0.00311   0.0350   0.5872   0.0177
  -2.750  -0.3573   0.01103   0.00285   0.0353   0.5815   0.0199
  -2.500  -0.3304   0.01085   0.00261   0.0355   0.5765   0.0224
  -2.250  -0.3045   0.01048   0.00237   0.0359   0.5714   0.0530
  -2.000  -0.2787   0.01012   0.00217   0.0363   0.5662   0.0976
  -1.750  -0.2529   0.00981   0.00200   0.0366   0.5614   0.1445
  -1.500  -0.2271   0.00948   0.00185   0.0370   0.5564   0.1977
  -1.250  -0.2024   0.00903   0.00171   0.0374   0.5515   0.2843
  -1.000  -0.1782   0.00859   0.00159   0.0380   0.5469   0.3781
  -0.750  -0.1580   0.00786   0.00147   0.0394   0.5422   0.5356
  -0.500  -0.1426   0.00705   0.00137   0.0420   0.5378   0.7140
  -0.250  -0.1159   0.00654   0.00136   0.0427   0.5334   0.8475
   0.000  -0.0362   0.00662   0.00156   0.0316   0.5266   0.9135
   0.250   0.0059   0.00679   0.00167   0.0288   0.5215   0.9310
   0.500   0.0394   0.00692   0.00177   0.0278   0.5165   0.9428
   0.750   0.0718   0.00705   0.00186   0.0269   0.5112   0.9526
   1.000   0.1035   0.00718   0.00193   0.0262   0.5064   0.9612
   1.250   0.1341   0.00729   0.00202   0.0258   0.5012   0.9687
   1.500   0.1697   0.00739   0.00209   0.0241   0.4958   0.9731
   1.750   0.2056   0.00749   0.00216   0.0224   0.4905   0.9778
   2.000   0.2373   0.00760   0.00226   0.0217   0.4846   0.9829
   2.500   0.3126   0.00768   0.00231   0.0174   0.4695   0.9883
   2.750   0.3473   0.00773   0.00234   0.0158   0.4612   0.9912
   3.000   0.3806   0.00780   0.00239   0.0146   0.4521   0.9938
   3.250   0.4151   0.00781   0.00241   0.0131   0.4417   0.9955
   3.500   0.4490   0.00783   0.00242   0.0117   0.4309   0.9973
   3.750   0.4823   0.00787   0.00245   0.0104   0.4195   0.9990
   4.000   0.5135   0.00793   0.00250   0.0096   0.4056   1.0000
   4.250   0.5396   0.00803   0.00259   0.0099   0.3913   1.0000
   4.500   0.5657   0.00814   0.00269   0.0101   0.3748   1.0000
   4.750   0.5919   0.00832   0.00281   0.0103   0.3508   1.0000
   5.000   0.6178   0.00873   0.00300   0.0102   0.2942   1.0000
   5.250   0.6434   0.00956   0.00343   0.0098   0.2056   1.0000
   5.500   0.6689   0.01007   0.00377   0.0098   0.1645   1.0000
   5.750   0.6942   0.01061   0.00415   0.0097   0.1259   1.0000
   6.000   0.7187   0.01134   0.00464   0.0097   0.0787   1.0000
   6.250   0.7431   0.01193   0.00509   0.0098   0.0498   1.0000
   6.500   0.7672   0.01252   0.00558   0.0100   0.0282   1.0000
   6.750   0.7907   0.01322   0.00620   0.0102   0.0113   1.0000
   7.000   0.8146   0.01370   0.00671   0.0106   0.0090   1.0000
   7.250   0.8380   0.01424   0.00731   0.0111   0.0076   1.0000
   7.500   0.8610   0.01481   0.00796   0.0116   0.0068   1.0000
   7.750   0.8839   0.01532   0.00854   0.0121   0.0062   1.0000
   8.000   0.9060   0.01591   0.00922   0.0127   0.0059   1.0000
   8.250   0.9274   0.01657   0.00998   0.0133   0.0056   1.0000
   8.500   0.9478   0.01730   0.01080   0.0141   0.0052   1.0000
   8.750   0.9673   0.01809   0.01167   0.0149   0.0050   1.0000
   9.000   0.9856   0.01897   0.01263   0.0158   0.0048   1.0000
   9.250   1.0018   0.01999   0.01375   0.0169   0.0046   1.0000
   9.500   1.0158   0.02113   0.01499   0.0182   0.0044   1.0000
   9.750   1.0282   0.02230   0.01626   0.0197   0.0043   1.0000
  10.000   1.0314   0.02420   0.01830   0.0220   0.0041   1.0000
  10.250   1.0341   0.02597   0.02020   0.0243   0.0040   1.0000
  10.500   1.0332   0.02747   0.02180   0.0270   0.0040   1.0000
  10.750   1.0312   0.02895   0.02340   0.0294   0.0039   1.0000
  11.000   1.0325   0.03062   0.02518   0.0309   0.0039   1.0000
  11.250   1.0340   0.03252   0.02719   0.0320   0.0039   1.0000
  11.500   1.0351   0.03465   0.02945   0.0328   0.0038   1.0000
  11.750   1.0367   0.03683   0.03175   0.0334   0.0038   1.0000
  12.000   1.0368   0.03927   0.03432   0.0338   0.0038   1.0000
  12.250   1.0356   0.04196   0.03716   0.0339   0.0038   1.0000
  12.500   1.0333   0.04487   0.04021   0.0339   0.0038   1.0000
  12.750   1.0301   0.04794   0.04342   0.0335   0.0037   1.0000
  13.000   1.0252   0.05133   0.04696   0.0329   0.0037   1.0000
  13.250   1.0189   0.05502   0.05079   0.0321   0.0037   1.0000
  13.500   1.0106   0.05910   0.05503   0.0308   0.0037   1.0000
  13.750   1.0025   0.06332   0.05940   0.0293   0.0037   1.0000
  14.000   0.9920   0.06808   0.06430   0.0275   0.0037   1.0000
  14.250   0.9793   0.07353   0.06990   0.0251   0.0037   1.0000
  14.500   0.9667   0.07933   0.07585   0.0223   0.0037   1.0000
  14.750   0.9549   0.08524   0.08189   0.0193   0.0037   1.0000
  15.000   0.9404   0.09203   0.08882   0.0158   0.0037   1.0000
  15.250   0.9205   0.10022   0.09716   0.0116   0.0037   1.0000
  15.500   0.9050   0.10790   0.10496   0.0077   0.0037   1.0000
  15.750   0.8855   0.11683   0.11401   0.0031   0.0038   1.0000
  16.000   0.8658   0.12639   0.12369  -0.0017   0.0038   1.0000
  16.250   0.8408   0.13770   0.13511  -0.0071   0.0039   1.0000
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