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EPPLER 585 AIRFOIL (e585-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 585 AIRFOIL (e585-il)
Reynolds number: 200,000
Max Cl/Cd: 78.63 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e585-il-200000-n5.txt
Download as CSV file: xf-e585-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 585 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1939   0.11656   0.11292  -0.0758   0.9608   0.0205
 -11.250  -0.1831   0.11239   0.10875  -0.0793   0.9538   0.0206
 -11.000  -0.1784   0.10506   0.10139  -0.0848   0.9475   0.0144
 -10.750  -0.1630   0.10138   0.09770  -0.0881   0.9417   0.0138
 -10.500  -0.1520   0.09622   0.09253  -0.0927   0.9349   0.0133
 -10.250  -0.1417   0.09035   0.08663  -0.0987   0.9281   0.0141
 -10.000  -0.1334   0.08382   0.08008  -0.1052   0.9196   0.0144
  -9.750  -0.1193   0.07955   0.07577  -0.1100   0.9113   0.0141
  -9.500  -0.1098   0.07418   0.07038  -0.1157   0.9016   0.0138
  -9.250  -0.1040   0.06891   0.06507  -0.1209   0.8902   0.0135
  -9.000  -0.1052   0.06248   0.05861  -0.1273   0.8779   0.0132
  -8.750  -0.1174   0.05575   0.05174  -0.1333   0.8648   0.0132
  -8.500  -0.1345   0.05112   0.04695  -0.1346   0.8533   0.0130
  -8.250  -0.1505   0.04761   0.04327  -0.1335   0.8429   0.0128
  -7.750  -0.1860   0.03522   0.02978  -0.1288   0.8265   0.0113
  -7.500  -0.1796   0.03245   0.02666  -0.1273   0.8210   0.0112
  -7.250  -0.1697   0.02995   0.02381  -0.1258   0.8152   0.0112
  -7.000  -0.1553   0.02756   0.02100  -0.1246   0.8105   0.0111
  -6.750  -0.1379   0.02549   0.01854  -0.1236   0.8061   0.0111
  -6.500  -0.1188   0.02373   0.01644  -0.1225   0.8012   0.0112
  -6.250  -0.0969   0.02220   0.01456  -0.1218   0.7971   0.0113
  -6.000  -0.0729   0.02088   0.01298  -0.1213   0.7937   0.0114
  -5.750  -0.0505   0.01980   0.01180  -0.1206   0.7894   0.0116
  -5.500  -0.0276   0.01892   0.01083  -0.1200   0.7851   0.0120
  -5.250  -0.0036   0.01815   0.00996  -0.1195   0.7814   0.0126
  -5.000   0.0212   0.01742   0.00910  -0.1192   0.7783   0.0133
  -4.750   0.0442   0.01681   0.00840  -0.1185   0.7741   0.0143
  -4.500   0.0675   0.01625   0.00780  -0.1180   0.7700   0.0156
  -4.250   0.0927   0.01585   0.00731  -0.1177   0.7665   0.0184
  -4.000   0.1186   0.01540   0.00679  -0.1176   0.7634   0.0230
  -3.750   0.1429   0.01492   0.00633  -0.1172   0.7597   0.0310
  -3.500   0.1669   0.01446   0.00597  -0.1168   0.7556   0.0537
  -3.250   0.1918   0.01398   0.00567  -0.1167   0.7521   0.1017
  -3.000   0.2168   0.01334   0.00540  -0.1169   0.7489   0.1976
  -2.750   0.2405   0.01249   0.00515  -0.1171   0.7457   0.3649
  -2.500   0.2588   0.01173   0.00537  -0.1155   0.7416   0.6069
  -2.250   0.2823   0.01189   0.00564  -0.1142   0.7379   0.6922
  -2.000   0.3089   0.01206   0.00573  -0.1136   0.7346   0.7246
  -1.750   0.3363   0.01223   0.00579  -0.1133   0.7319   0.7455
  -1.500   0.3602   0.01241   0.00593  -0.1123   0.7277   0.7604
  -1.250   0.3843   0.01260   0.00607  -0.1113   0.7237   0.7758
  -1.000   0.4071   0.01285   0.00628  -0.1097   0.7201   0.7949
  -0.750   0.4310   0.01302   0.00639  -0.1084   0.7172   0.8079
  -0.500   0.4566   0.01309   0.00640  -0.1081   0.7129   0.8150
  -0.250   0.4816   0.01312   0.00640  -0.1076   0.7086   0.8181
   0.000   0.5089   0.01313   0.00634  -0.1076   0.7048   0.8212
   0.250   0.5383   0.01314   0.00624  -0.1081   0.7018   0.8243
   0.500   0.5645   0.01319   0.00627  -0.1081   0.6971   0.8278
   0.750   0.5914   0.01321   0.00626  -0.1082   0.6928   0.8304
   1.000   0.6186   0.01322   0.00623  -0.1082   0.6890   0.8325
   1.250   0.6469   0.01324   0.00620  -0.1084   0.6857   0.8349
   1.500   0.6713   0.01331   0.00629  -0.1080   0.6804   0.8376
   1.750   0.6985   0.01334   0.00629  -0.1082   0.6758   0.8402
   2.000   0.7281   0.01335   0.00625  -0.1087   0.6719   0.8431
   2.250   0.7528   0.01341   0.00635  -0.1084   0.6663   0.8457
   2.500   0.7782   0.01344   0.00638  -0.1081   0.6609   0.8478
   2.750   0.8064   0.01345   0.00635  -0.1083   0.6566   0.8499
   3.000   0.8299   0.01353   0.00649  -0.1077   0.6504   0.8528
   3.250   0.8562   0.01357   0.00655  -0.1077   0.6448   0.8559
   3.500   0.8840   0.01361   0.00658  -0.1079   0.6395   0.8587
   3.750   0.9072   0.01368   0.00671  -0.1073   0.6324   0.8612
   4.000   0.9339   0.01369   0.00670  -0.1072   0.6267   0.8634
   4.250   0.9558   0.01378   0.00688  -0.1063   0.6188   0.8665
   4.500   0.9819   0.01382   0.00692  -0.1061   0.6122   0.8697
   4.750   1.0048   0.01393   0.00709  -0.1055   0.6039   0.8733
   5.000   1.0302   0.01397   0.00714  -0.1052   0.5966   0.8761
   5.250   1.0504   0.01408   0.00734  -0.1039   0.5873   0.8793
   5.500   1.0732   0.01417   0.00746  -0.1032   0.5786   0.8827
   5.750   1.0955   0.01428   0.00761  -0.1023   0.5686   0.8866
   6.000   1.1158   0.01442   0.00780  -0.1011   0.5577   0.8908
   6.250   1.1349   0.01455   0.00797  -0.0996   0.5465   0.8953
   6.500   1.1543   0.01471   0.00816  -0.0983   0.5343   0.9002
   6.750   1.1723   0.01491   0.00838  -0.0967   0.5210   0.9053
   7.000   1.1861   0.01510   0.00859  -0.0942   0.5067   0.9114
   7.250   1.2003   0.01537   0.00888  -0.0919   0.4913   0.9188
   7.500   1.2121   0.01566   0.00919  -0.0892   0.4754   0.9287
   7.750   1.2241   0.01601   0.00957  -0.0867   0.4584   0.9433
   8.000   1.2385   0.01639   0.00996  -0.0849   0.4398   1.0000
   8.250   1.2519   0.01703   0.01055  -0.0831   0.4202   1.0000
   8.500   1.2639   0.01775   0.01122  -0.0813   0.4011   1.0000
   8.750   1.2745   0.01854   0.01198  -0.0793   0.3808   1.0000
   9.000   1.2830   0.01947   0.01285  -0.0771   0.3605   1.0000
   9.250   1.2905   0.02049   0.01381  -0.0748   0.3410   1.0000
   9.500   1.2979   0.02156   0.01485  -0.0727   0.3215   1.0000
   9.750   1.3043   0.02275   0.01600  -0.0706   0.3026   1.0000
  10.000   1.3093   0.02408   0.01727  -0.0685   0.2838   1.0000
  10.250   1.3152   0.02542   0.01860  -0.0666   0.2656   1.0000
  10.500   1.3203   0.02687   0.02001  -0.0647   0.2469   1.0000
  10.750   1.3251   0.02840   0.02151  -0.0629   0.2295   1.0000
  11.000   1.3288   0.03007   0.02313  -0.0612   0.2121   1.0000
  11.500   1.3373   0.03349   0.02651  -0.0582   0.1801   1.0000
  11.750   1.3414   0.03532   0.02833  -0.0568   0.1645   1.0000
  12.000   1.3452   0.03722   0.03022  -0.0555   0.1497   1.0000
  12.250   1.3486   0.03920   0.03219  -0.0544   0.1355   1.0000
  12.500   1.3523   0.04124   0.03422  -0.0533   0.1227   1.0000
  12.750   1.3554   0.04339   0.03637  -0.0523   0.1102   1.0000
  13.000   1.3581   0.04564   0.03862  -0.0514   0.0989   1.0000
  13.250   1.3603   0.04801   0.04099  -0.0506   0.0882   1.0000
  13.500   1.3631   0.05039   0.04339  -0.0500   0.0777   1.0000
  13.750   1.3653   0.05288   0.04593  -0.0494   0.0683   1.0000
  14.000   1.3670   0.05551   0.04859  -0.0489   0.0600   1.0000
  14.250   1.3676   0.05833   0.05143  -0.0485   0.0526   1.0000
  14.500   1.3680   0.06125   0.05439  -0.0483   0.0461   1.0000
  14.750   1.3691   0.06416   0.05737  -0.0481   0.0404   1.0000
  15.000   1.3678   0.06744   0.06070  -0.0481   0.0360   1.0000
  15.250   1.3683   0.07058   0.06394  -0.0482   0.0318   1.0000
  15.500   1.3660   0.07417   0.06759  -0.0485   0.0285   1.0000
  15.750   1.3654   0.07760   0.07113  -0.0489   0.0253   1.0000
  16.000   1.3611   0.08162   0.07522  -0.0495   0.0230   1.0000
  16.250   1.3602   0.08526   0.07903  -0.0501   0.0207   1.0000
  16.500   1.3560   0.08945   0.08330  -0.0510   0.0187   1.0000
  16.750   1.3521   0.09369   0.08767  -0.0521   0.0171   1.0000
  17.000   1.3485   0.09796   0.09206  -0.0533   0.0154   1.0000
  17.250   1.3424   0.10270   0.09690  -0.0548   0.0143   1.0000
  17.500   1.3376   0.10733   0.10168  -0.0563   0.0131   1.0000
  17.750   1.3327   0.11205   0.10654  -0.0581   0.0121   1.0000
  18.000   1.3262   0.11712   0.11173  -0.0601   0.0114   1.0000
  18.250   1.3178   0.12260   0.11731  -0.0625   0.0108   1.0000
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