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EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E853 AIRFOIL (e853-il)
Reynolds number: 200,000
Max Cl/Cd: 85.88 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e853-il-200000.txt
Download as CSV file: xf-e853-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E853 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4180   0.08791   0.08469  -0.0535   1.0000   0.0439
  -8.750  -0.4332   0.08339   0.08022  -0.0555   1.0000   0.0439
  -8.500  -0.4521   0.08030   0.07719  -0.0553   1.0000   0.0439
  -8.250  -0.4780   0.07838   0.07534  -0.0529   1.0000   0.0439
  -8.000  -0.5044   0.07650   0.07350  -0.0512   1.0000   0.0439
  -7.750  -0.4971   0.07032   0.06704  -0.0616   0.9932   0.0441
  -7.500  -0.4912   0.06033   0.05701  -0.0685   0.9865   0.0455
  -7.250  -0.4660   0.05589   0.05255  -0.0728   0.9827   0.0471
  -7.000  -0.3828   0.03658   0.03321  -0.0825   0.9622   0.0530
  -6.750  -0.3667   0.02980   0.02585  -0.0890   0.9566   0.0592
  -6.500  -0.3923   0.03324   0.02791  -0.0860   0.9606   0.0209
  -6.250  -0.3586   0.02825   0.02234  -0.0893   0.9574   0.0199
  -6.000  -0.3307   0.02518   0.01881  -0.0901   0.9499   0.0197
  -5.750  -0.2940   0.02264   0.01587  -0.0921   0.9465   0.0203
  -5.500  -0.2561   0.02037   0.01334  -0.0946   0.9442   0.0247
  -5.250  -0.2273   0.01907   0.01194  -0.0950   0.9363   0.0283
  -5.000  -0.1900   0.01709   0.00986  -0.0970   0.9331   0.0347
  -4.750  -0.1494   0.01565   0.00844  -0.1001   0.9310   0.0591
  -4.500  -0.1190   0.01457   0.00747  -0.1012   0.9234   0.0980
  -4.250  -0.0813   0.01224   0.00641  -0.1052   0.9203   0.3585
  -4.000  -0.0405   0.01198   0.00625  -0.1077   0.9176   0.4674
  -3.750  -0.0100   0.01201   0.00623  -0.1081   0.9098   0.5059
  -3.500   0.0281   0.01201   0.00612  -0.1099   0.9056   0.5392
  -3.250   0.0608   0.01200   0.00607  -0.1107   0.8992   0.5589
  -3.000   0.0950   0.01195   0.00592  -0.1118   0.8932   0.5757
  -2.750   0.1292   0.01192   0.00581  -0.1129   0.8877   0.5924
  -2.500   0.1591   0.01196   0.00579  -0.1131   0.8802   0.6099
  -2.250   0.1914   0.01193   0.00572  -0.1138   0.8743   0.6244
  -2.000   0.2200   0.01192   0.00565  -0.1139   0.8666   0.6348
  -1.750   0.2514   0.01185   0.00553  -0.1146   0.8607   0.6432
  -1.500   0.2797   0.01184   0.00545  -0.1147   0.8530   0.6521
  -1.250   0.3103   0.01179   0.00537  -0.1153   0.8473   0.6598
  -1.000   0.3372   0.01181   0.00534  -0.1152   0.8399   0.6680
  -0.750   0.3686   0.01178   0.00526  -0.1159   0.8348   0.6767
  -0.500   0.3937   0.01182   0.00532  -0.1155   0.8271   0.6845
  -0.250   0.4243   0.01182   0.00527  -0.1161   0.8221   0.6938
   0.000   0.4497   0.01188   0.00538  -0.1157   0.8152   0.7024
   0.250   0.4784   0.01190   0.00539  -0.1159   0.8097   0.7116
   0.500   0.5056   0.01197   0.00548  -0.1158   0.8038   0.7220
   0.750   0.5325   0.01202   0.00558  -0.1157   0.7979   0.7325
   1.000   0.5615   0.01205   0.00563  -0.1159   0.7933   0.7433
   1.250   0.5858   0.01215   0.00582  -0.1153   0.7866   0.7551
   1.500   0.6138   0.01218   0.00590  -0.1154   0.7816   0.7681
   1.750   0.6389   0.01228   0.00611  -0.1149   0.7757   0.7824
   2.000   0.6647   0.01233   0.00625  -0.1144   0.7699   0.7983
   2.250   0.6913   0.01237   0.00637  -0.1141   0.7648   0.8166
   2.500   0.7132   0.01242   0.00656  -0.1128   0.7576   0.8368
   2.750   0.7386   0.01238   0.00662  -0.1120   0.7521   0.8619
   3.000   0.7565   0.01235   0.00677  -0.1097   0.7438   0.8962
   3.250   0.7857   0.01219   0.00671  -0.1095   0.7368   0.9556
   3.500   0.8208   0.01217   0.00671  -0.1112   0.7269   1.0000
   3.750   0.8490   0.01218   0.00675  -0.1113   0.7150   1.0000
   4.000   0.8765   0.01213   0.00669  -0.1111   0.7015   1.0000
   4.250   0.9032   0.01212   0.00670  -0.1106   0.6886   1.0000
   4.500   0.9295   0.01215   0.00678  -0.1102   0.6764   1.0000
   4.750   0.9552   0.01217   0.00684  -0.1096   0.6629   1.0000
   5.000   0.9801   0.01217   0.00693  -0.1087   0.6474   1.0000
   5.250   1.0045   0.01215   0.00694  -0.1077   0.6292   1.0000
   5.500   1.0260   0.01217   0.00704  -0.1062   0.6055   1.0000
   5.750   1.0467   0.01222   0.00708  -0.1045   0.5741   1.0000
   6.000   1.0641   0.01239   0.00720  -0.1021   0.5248   1.0000
   6.250   1.0743   0.01301   0.00742  -0.0986   0.4354   1.0000
   6.500   1.0720   0.01454   0.00820  -0.0934   0.3121   1.0000
   6.750   1.0697   0.01633   0.00931  -0.0887   0.2036   1.0000
   7.000   1.0715   0.01797   0.01046  -0.0848   0.1303   1.0000
   7.250   1.0755   0.01936   0.01163  -0.0810   0.0924   1.0000
   7.500   1.0798   0.02076   0.01286  -0.0774   0.0692   1.0000
   7.750   1.0874   0.02203   0.01412  -0.0743   0.0532   1.0000
   8.000   1.0942   0.02343   0.01551  -0.0712   0.0411   1.0000
   8.250   1.1000   0.02501   0.01709  -0.0682   0.0319   1.0000
   8.500   1.1073   0.02660   0.01870  -0.0655   0.0256   1.0000
   8.750   1.1161   0.02863   0.02083  -0.0629   0.0216   1.0000
   9.000   1.1290   0.02972   0.02197  -0.0613   0.0180   1.0000
   9.250   1.1481   0.03344   0.02576  -0.0603   0.0155   1.0000
   9.500   1.1696   0.03539   0.02793  -0.0594   0.0149   1.0000
   9.750   1.1930   0.03809   0.03092  -0.0588   0.0145   1.0000
  10.000   1.2115   0.04129   0.03447  -0.0577   0.0143   1.0000
  10.250   1.2217   0.04482   0.03838  -0.0558   0.0142   1.0000
  10.500   1.2240   0.04843   0.04241  -0.0532   0.0144   1.0000
  10.750   1.2198   0.05217   0.04648  -0.0503   0.0146   1.0000
  11.000   1.2106   0.05615   0.05078  -0.0474   0.0148   1.0000
  11.250   1.1977   0.06043   0.05535  -0.0449   0.0150   1.0000
  12.500   1.1008   0.08680   0.08327  -0.0417   0.0191   1.0000
  12.750   1.0756   0.09381   0.09044  -0.0444   0.0194   1.0000
  13.000   1.0513   0.10138   0.09818  -0.0482   0.0196   1.0000
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