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EPPLER 585 AIRFOIL (e585-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 585 AIRFOIL (e585-il)
Reynolds number: 1,000,000
Max Cl/Cd: 131.28 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e585-il-1000000-n5.txt
Download as CSV file: xf-e585-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.0928   0.09582   0.09327  -0.1158   0.8381   0.0028
 -11.500  -0.0934   0.09183   0.08924  -0.1171   0.8260   0.0029
 -11.000  -0.4270   0.03028   0.02693  -0.1379   0.7944   0.0027
 -10.750  -0.4211   0.02957   0.02617  -0.1361   0.7878   0.0028
 -10.500  -0.3945   0.03051   0.02721  -0.1358   0.7821   0.0029
 -10.250  -0.3901   0.02975   0.02635  -0.1336   0.7760   0.0030
 -10.000  -0.3955   0.02711   0.02345  -0.1311   0.7699   0.0030
  -9.750  -0.3981   0.02433   0.02032  -0.1284   0.7643   0.0030
  -9.500  -0.3894   0.02247   0.01820  -0.1268   0.7600   0.0031
  -9.250  -0.3761   0.02094   0.01645  -0.1255   0.7557   0.0032
  -9.000  -0.3596   0.01972   0.01503  -0.1244   0.7513   0.0032
  -8.500  -0.3208   0.01774   0.01271  -0.1229   0.7440   0.0034
  -8.250  -0.2993   0.01691   0.01173  -0.1223   0.7404   0.0035
  -8.000  -0.2779   0.01601   0.01067  -0.1217   0.7367   0.0036
  -7.750  -0.2558   0.01520   0.00970  -0.1211   0.7331   0.0036
  -7.500  -0.2324   0.01453   0.00892  -0.1207   0.7301   0.0037
  -7.250  -0.2082   0.01394   0.00822  -0.1204   0.7270   0.0038
  -7.000  -0.1840   0.01335   0.00753  -0.1200   0.7236   0.0038
  -6.750  -0.1594   0.01285   0.00693  -0.1197   0.7203   0.0039
  -6.500  -0.1346   0.01239   0.00639  -0.1194   0.7172   0.0039
  -6.250  -0.1090   0.01196   0.00590  -0.1193   0.7145   0.0040
  -6.000  -0.0830   0.01160   0.00548  -0.1192   0.7115   0.0041
  -5.750  -0.0565   0.01135   0.00519  -0.1192   0.7083   0.0042
  -5.500  -0.0314   0.01084   0.00460  -0.1189   0.7052   0.0044
  -5.250  -0.0055   0.01048   0.00420  -0.1188   0.7024   0.0046
  -5.000   0.0213   0.01020   0.00388  -0.1188   0.6998   0.0048
  -4.750   0.0483   0.00993   0.00358  -0.1189   0.6968   0.0050
  -4.500   0.0755   0.00969   0.00331  -0.1189   0.6937   0.0052
  -4.250   0.1027   0.00948   0.00306  -0.1190   0.6908   0.0055
  -4.000   0.1300   0.00930   0.00283  -0.1190   0.6879   0.0059
  -3.750   0.1575   0.00912   0.00262  -0.1192   0.6851   0.0067
  -3.500   0.1854   0.00893   0.00243  -0.1193   0.6822   0.0089
  -3.250   0.2132   0.00876   0.00227  -0.1195   0.6791   0.0145
  -3.000   0.2408   0.00858   0.00214  -0.1197   0.6758   0.0262
  -2.750   0.2683   0.00842   0.00202  -0.1199   0.6726   0.0432
  -2.500   0.2960   0.00819   0.00191  -0.1202   0.6694   0.0791
  -2.250   0.3237   0.00786   0.00181  -0.1206   0.6658   0.1466
  -2.000   0.3514   0.00754   0.00172  -0.1210   0.6620   0.2237
  -1.750   0.3792   0.00726   0.00164  -0.1214   0.6583   0.3022
  -1.500   0.4073   0.00696   0.00156  -0.1219   0.6551   0.3911
  -1.250   0.4359   0.00631   0.00146  -0.1228   0.6517   0.5738
  -1.000   0.4644   0.00613   0.00150  -0.1232   0.6479   0.6591
  -0.750   0.4927   0.00614   0.00153  -0.1234   0.6441   0.6853
  -0.500   0.5210   0.00618   0.00155  -0.1236   0.6405   0.7000
  -0.250   0.5496   0.00620   0.00159  -0.1238   0.6365   0.7126
   0.000   0.5778   0.00625   0.00163  -0.1240   0.6314   0.7268
   0.500   0.6337   0.00640   0.00175  -0.1242   0.6214   0.7495
   0.750   0.6620   0.00646   0.00177  -0.1244   0.6160   0.7523
   1.000   0.6895   0.00651   0.00180  -0.1245   0.6109   0.7541
   1.250   0.7177   0.00655   0.00183  -0.1247   0.6054   0.7559
   1.500   0.7451   0.00662   0.00187  -0.1248   0.5990   0.7577
   1.750   0.7727   0.00668   0.00192  -0.1249   0.5925   0.7595
   2.000   0.7999   0.00676   0.00197  -0.1250   0.5849   0.7612
   2.250   0.8272   0.00684   0.00203  -0.1251   0.5778   0.7632
   2.500   0.8541   0.00694   0.00209  -0.1251   0.5696   0.7651
   2.750   0.8810   0.00703   0.00216  -0.1251   0.5617   0.7668
   3.000   0.9071   0.00715   0.00224  -0.1249   0.5526   0.7684
   3.250   0.9336   0.00725   0.00233  -0.1249   0.5430   0.7700
   3.500   0.9592   0.00737   0.00243  -0.1246   0.5328   0.7716
   3.750   0.9842   0.00752   0.00256  -0.1243   0.5214   0.7735
   4.000   1.0091   0.00769   0.00268  -0.1239   0.5084   0.7755
   4.250   1.0332   0.00787   0.00282  -0.1234   0.4938   0.7775
   4.750   1.0793   0.00833   0.00317  -0.1221   0.4606   0.7812
   5.000   1.1014   0.00859   0.00336  -0.1212   0.4425   0.7830
   5.250   1.1226   0.00887   0.00357  -0.1202   0.4244   0.7848
   5.500   1.1430   0.00916   0.00382  -0.1190   0.4060   0.7869
   5.750   1.1624   0.00948   0.00407  -0.1177   0.3879   0.7891
   6.000   1.1803   0.00981   0.00433  -0.1160   0.3681   0.7914
   6.250   1.1960   0.01015   0.00461  -0.1140   0.3489   0.7938
   6.500   1.2106   0.01054   0.00493  -0.1117   0.3296   0.7961
   6.750   1.2255   0.01096   0.00527  -0.1096   0.3110   0.7983
   7.000   1.2397   0.01140   0.00564  -0.1073   0.2917   0.8006
   7.250   1.2547   0.01181   0.00603  -0.1053   0.2758   0.8031
   7.500   1.2678   0.01231   0.00646  -0.1030   0.2577   0.8060
   7.750   1.2798   0.01287   0.00695  -0.1006   0.2398   0.8091
   8.000   1.2924   0.01342   0.00745  -0.0983   0.2235   0.8121
   8.250   1.3044   0.01402   0.00799  -0.0961   0.2072   0.8147
   8.500   1.3150   0.01468   0.00861  -0.0936   0.1898   0.8177
   8.750   1.3254   0.01539   0.00927  -0.0913   0.1741   0.8210
   9.000   1.3351   0.01617   0.01000  -0.0889   0.1582   0.8245
   9.250   1.3439   0.01704   0.01081  -0.0866   0.1425   0.8281
   9.500   1.3501   0.01808   0.01178  -0.0840   0.1235   0.8320
   9.750   1.3588   0.01904   0.01270  -0.0818   0.1098   0.8365
  10.000   1.3624   0.02034   0.01391  -0.0792   0.0899   0.8415
  10.250   1.3690   0.02153   0.01504  -0.0770   0.0759   0.8462
  10.500   1.3747   0.02280   0.01627  -0.0748   0.0615   0.8516
  10.750   1.3827   0.02399   0.01745  -0.0730   0.0522   0.8575
  11.000   1.3892   0.02530   0.01874  -0.0712   0.0422   0.8639
  11.250   1.3968   0.02658   0.02003  -0.0695   0.0352   0.8720
  11.500   1.4035   0.02792   0.02139  -0.0678   0.0286   0.8822
  11.750   1.4107   0.02922   0.02273  -0.0661   0.0238   0.8971
  12.000   1.4166   0.03037   0.02401  -0.0641   0.0200   0.9368
  12.500   1.4334   0.03339   0.02707  -0.0622   0.0128   1.0000
  12.750   1.4415   0.03494   0.02864  -0.0611   0.0105   1.0000
  13.000   1.4502   0.03646   0.03021  -0.0602   0.0090   1.0000
  13.250   1.4577   0.03813   0.03191  -0.0593   0.0072   1.0000
  13.500   1.4652   0.03985   0.03366  -0.0585   0.0060   1.0000
  13.750   1.4719   0.04168   0.03554  -0.0577   0.0046   1.0000
  14.000   1.4798   0.04343   0.03734  -0.0570   0.0041   1.0000
  14.250   1.4851   0.04549   0.03943  -0.0563   0.0031   1.0000
  14.500   1.4921   0.04741   0.04141  -0.0558   0.0027   1.0000
  14.750   1.4982   0.04947   0.04354  -0.0553   0.0022   1.0000
  15.000   1.5020   0.05183   0.04596  -0.0548   0.0015   1.0000
  15.250   1.5087   0.05392   0.04812  -0.0545   0.0015   1.0000
  15.500   1.5111   0.05654   0.05080  -0.0541   0.0010   1.0000
  15.750   1.5152   0.05903   0.05336  -0.0540   0.0008   1.0000
  16.000   1.5174   0.06180   0.05620  -0.0538   0.0006   1.0000
  16.250   1.5214   0.06440   0.05888  -0.0538   0.0006   1.0000
  16.500   1.5220   0.06748   0.06205  -0.0539   0.0004   1.0000
  16.750   1.5236   0.07050   0.06515  -0.0542   0.0003   1.0000
  17.000   1.5250   0.07362   0.06836  -0.0545   0.0003   1.0000
  17.250   1.5256   0.07690   0.07173  -0.0549   0.0003   1.0000
  17.500   1.5253   0.08038   0.07530  -0.0555   0.0002   1.0000
  17.750   1.5222   0.08432   0.07934  -0.0563   0.0002   1.0000
  18.000   1.5226   0.08781   0.08292  -0.0571   0.0002   1.0000
  18.250   1.5182   0.09212   0.08733  -0.0581   0.0002   1.0000
  18.500   1.5150   0.09630   0.09161  -0.0593   0.0001   1.0000
  18.750   1.5092   0.10095   0.09639  -0.0608   0.0001   1.0000
  19.000   1.5052   0.10538   0.10092  -0.0623   0.0001   1.0000
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