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EPPLER 856 AIRFOIL (e856-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 856 AIRFOIL (e856-il)
Reynolds number: 200,000
Max Cl/Cd: 64.76 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e856-il-200000.txt
Download as CSV file: xf-e856-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 856 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5332   0.07536   0.07140  -0.0772   1.0000   0.0264
 -12.250  -0.5584   0.07013   0.06609  -0.0793   1.0000   0.0263
 -12.000  -0.5680   0.06673   0.06270  -0.0791   1.0000   0.0260
 -11.750  -0.5887   0.06295   0.05886  -0.0794   1.0000   0.0258
 -11.500  -0.6158   0.05936   0.05520  -0.0790   1.0000   0.0257
 -11.250  -0.6398   0.05680   0.05262  -0.0773   1.0000   0.0255
 -11.000  -0.6613   0.05308   0.04870  -0.0797   0.9966   0.0256
 -10.750  -0.6617   0.04824   0.04351  -0.0865   0.9865   0.0255
 -10.500  -0.6555   0.04374   0.03852  -0.0911   0.9757   0.0258
 -10.250  -0.6395   0.03988   0.03421  -0.0941   0.9659   0.0260
 -10.000  -0.6187   0.03653   0.03038  -0.0964   0.9570   0.0263
  -9.750  -0.5907   0.03363   0.02732  -0.0984   0.9507   0.0269
  -9.500  -0.5636   0.03174   0.02536  -0.0996   0.9423   0.0278
  -9.250  -0.5295   0.02986   0.02335  -0.1019   0.9370   0.0291
  -9.000  -0.5026   0.02813   0.02135  -0.1026   0.9277   0.0308
  -8.750  -0.4682   0.02631   0.01959  -0.1047   0.9229   0.0329
  -8.500  -0.4390   0.02514   0.01826  -0.1057   0.9139   0.0362
  -8.250  -0.4054   0.02353   0.01674  -0.1076   0.9082   0.0400
  -8.000  -0.3749   0.02203   0.01521  -0.1089   0.8994   0.0446
  -7.750  -0.3371   0.02065   0.01383  -0.1117   0.8923   0.0525
  -7.500  -0.3001   0.01942   0.01260  -0.1143   0.8824   0.0628
  -7.250  -0.2526   0.01828   0.01138  -0.1190   0.8747   0.0780
  -7.000  -0.2170   0.01710   0.01029  -0.1216   0.8614   0.0948
  -6.750  -0.1799   0.01618   0.00934  -0.1242   0.8474   0.1181
  -6.500  -0.1478   0.01520   0.00846  -0.1260   0.8325   0.1503
  -6.250  -0.1200   0.01423   0.00767  -0.1270   0.8173   0.2015
  -6.000  -0.0948   0.01341   0.00717  -0.1274   0.8028   0.2914
  -5.750  -0.0661   0.01329   0.00710  -0.1277   0.7891   0.3568
  -5.500  -0.0400   0.01341   0.00712  -0.1272   0.7745   0.3893
  -5.250  -0.0136   0.01360   0.00721  -0.1266   0.7609   0.4115
  -5.000   0.0137   0.01383   0.00729  -0.1263   0.7482   0.4296
  -4.750   0.0423   0.01407   0.00736  -0.1262   0.7369   0.4454
  -4.500   0.0672   0.01426   0.00739  -0.1255   0.7248   0.4592
  -4.250   0.0939   0.01444   0.00754  -0.1249   0.7141   0.4696
  -4.000   0.1217   0.01457   0.00751  -0.1248   0.7043   0.4801
  -3.750   0.1467   0.01470   0.00757  -0.1240   0.6935   0.4896
  -3.500   0.1746   0.01481   0.00754  -0.1239   0.6847   0.4985
  -3.250   0.1996   0.01492   0.00759  -0.1232   0.6749   0.5078
  -3.000   0.2274   0.01504   0.00761  -0.1231   0.6671   0.5167
  -2.750   0.2526   0.01517   0.00767  -0.1225   0.6583   0.5267
  -2.500   0.2809   0.01526   0.00765  -0.1225   0.6512   0.5343
  -2.250   0.3056   0.01529   0.00766  -0.1218   0.6428   0.5412
  -2.000   0.3342   0.01532   0.00750  -0.1221   0.6360   0.5480
  -1.750   0.3595   0.01532   0.00752  -0.1215   0.6287   0.5528
  -1.500   0.3867   0.01535   0.00747  -0.1214   0.6222   0.5587
  -1.250   0.4157   0.01542   0.00737  -0.1218   0.6166   0.5651
  -1.000   0.4404   0.01540   0.00740  -0.1212   0.6097   0.5695
  -0.750   0.4681   0.01545   0.00737  -0.1213   0.6040   0.5752
  -0.500   0.4962   0.01555   0.00734  -0.1215   0.5986   0.5818
  -0.250   0.5214   0.01555   0.00739  -0.1210   0.5927   0.5863
   0.000   0.5492   0.01561   0.00741  -0.1211   0.5877   0.5920
   0.250   0.5788   0.01576   0.00742  -0.1216   0.5832   0.5989
   0.500   0.6027   0.01578   0.00752  -0.1209   0.5777   0.6040
   0.750   0.6294   0.01585   0.00758  -0.1208   0.5726   0.6098
   1.000   0.6590   0.01599   0.00759  -0.1213   0.5684   0.6171
   1.250   0.6846   0.01609   0.00776  -0.1209   0.5640   0.6228
   1.500   0.7098   0.01620   0.00791  -0.1205   0.5594   0.6297
   1.750   0.7372   0.01630   0.00798  -0.1206   0.5551   0.6366
   2.000   0.7663   0.01644   0.00809  -0.1209   0.5513   0.6437
   2.250   0.7915   0.01661   0.00829  -0.1206   0.5470   0.6523
   2.500   0.8156   0.01672   0.00850  -0.1200   0.5427   0.6595
   2.750   0.8427   0.01687   0.00864  -0.1200   0.5389   0.6688
   3.000   0.8710   0.01701   0.00880  -0.1202   0.5355   0.6773
   3.250   0.8988   0.01724   0.00903  -0.1204   0.5321   0.6881
   3.500   0.9202   0.01738   0.00932  -0.1193   0.5278   0.6984
   3.750   0.9448   0.01753   0.00955  -0.1189   0.5238   0.7097
   4.000   0.9719   0.01769   0.00974  -0.1189   0.5205   0.7232
   4.250   1.0011   0.01790   0.00996  -0.1193   0.5176   0.7387
   4.500   1.0240   0.01813   0.01033  -0.1185   0.5142   0.7555
   4.750   1.0439   0.01829   0.01067  -0.1171   0.5102   0.7745
   5.000   1.0659   0.01841   0.01093  -0.1161   0.5065   0.7979
   5.250   1.0896   0.01851   0.01115  -0.1152   0.5035   0.8303
   5.500   1.1151   0.01860   0.01134  -0.1146   0.5008   0.8843
   5.750   1.1498   0.01886   0.01177  -0.1165   0.4972   1.0000
   6.000   1.1720   0.01922   0.01219  -0.1159   0.4931   1.0000
   6.250   1.1972   0.01955   0.01252  -0.1158   0.4896   1.0000
   6.500   1.2257   0.01986   0.01281  -0.1163   0.4866   1.0000
   6.750   1.2582   0.02023   0.01310  -0.1175   0.4837   1.0000
   7.000   1.2756   0.02069   0.01368  -0.1159   0.4799   1.0000
   7.250   1.2945   0.02110   0.01420  -0.1146   0.4759   1.0000
   7.500   1.3183   0.02141   0.01454  -0.1141   0.4722   1.0000
   7.750   1.3480   0.02165   0.01476  -0.1147   0.4689   1.0000
   8.000   1.3753   0.02206   0.01518  -0.1149   0.4654   1.0000
   8.250   1.3866   0.02250   0.01578  -0.1123   0.4606   1.0000
   8.500   1.4075   0.02273   0.01607  -0.1112   0.4560   1.0000
   8.750   1.4387   0.02281   0.01611  -0.1120   0.4519   1.0000
   9.000   1.4563   0.02317   0.01655  -0.1104   0.4470   1.0000
   9.250   1.4682   0.02344   0.01694  -0.1077   0.4415   1.0000
   9.500   1.4953   0.02340   0.01687  -0.1077   0.4363   1.0000
   9.750   1.5161   0.02365   0.01716  -0.1066   0.4314   1.0000
  10.000   1.5223   0.02399   0.01766  -0.1030   0.4259   1.0000
  10.250   1.5448   0.02403   0.01770  -0.1022   0.4207   1.0000
  10.500   1.5673   0.02420   0.01789  -0.1015   0.4157   1.0000
  10.750   1.5642   0.02461   0.01849  -0.0962   0.4103   1.0000
  11.000   1.5800   0.02469   0.01859  -0.0943   0.4049   1.0000
  11.250   1.5964   0.02486   0.01878  -0.0925   0.3994   1.0000
  11.500   1.5915   0.02538   0.01947  -0.0873   0.3935   1.0000
  11.750   1.6067   0.02545   0.01955  -0.0854   0.3874   1.0000
  12.000   1.6074   0.02599   0.02021  -0.0814   0.3812   1.0000
  12.250   1.6078   0.02654   0.02086  -0.0776   0.3744   1.0000
  12.500   1.6167   0.02691   0.02125  -0.0751   0.3676   1.0000
  12.750   1.6083   0.02796   0.02246  -0.0707   0.3600   1.0000
  13.000   1.6140   0.02858   0.02310  -0.0681   0.3522   1.0000
  13.250   1.6042   0.03005   0.02472  -0.0643   0.3436   1.0000
  13.500   1.6024   0.03131   0.02604  -0.0616   0.3346   1.0000
  13.750   1.5979   0.03287   0.02765  -0.0589   0.3246   1.0000
  14.000   1.5880   0.03505   0.02995  -0.0563   0.3137   1.0000
  14.250   1.5796   0.03734   0.03229  -0.0541   0.3020   1.0000
  14.500   1.5695   0.03998   0.03494  -0.0522   0.2893   1.0000
  14.750   1.5568   0.04308   0.03805  -0.0505   0.2754   1.0000
  15.000   1.5419   0.04662   0.04160  -0.0492   0.2607   1.0000
  15.250   1.5253   0.05058   0.04554  -0.0482   0.2453   1.0000
  15.500   1.5079   0.05484   0.04976  -0.0474   0.2300   1.0000
  15.750   1.4904   0.05931   0.05418  -0.0470   0.2153   1.0000
  16.000   1.4734   0.06391   0.05873  -0.0468   0.2014   1.0000
  16.250   1.4579   0.06850   0.06326  -0.0468   0.1885   1.0000
  16.500   1.4436   0.07312   0.06784  -0.0471   0.1762   1.0000
  16.750   1.4319   0.07757   0.07229  -0.0475   0.1648   1.0000
  17.000   1.4219   0.08188   0.07659  -0.0481   0.1545   1.0000
  17.250   1.4122   0.08619   0.08084  -0.0487   0.1452   1.0000
  17.500   1.4041   0.09043   0.08510  -0.0494   0.1360   1.0000
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