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EPPLER 585 AIRFOIL (e585-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 585 AIRFOIL (e585-il)
Reynolds number: 1,000,000
Max Cl/Cd: 146.09 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e585-il-1000000.txt
Download as CSV file: xf-e585-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.0604   0.07972   0.07764  -0.1257   0.8984   0.0086
 -10.250  -0.0603   0.07484   0.07263  -0.1283   0.8732   0.0086
  -7.500  -0.2065   0.01910   0.01429  -0.1254   0.7698   0.0064
  -7.250  -0.1870   0.01780   0.01282  -0.1247   0.7658   0.0067
  -7.000  -0.1655   0.01659   0.01138  -0.1241   0.7619   0.0068
  -6.750  -0.1422   0.01565   0.01033  -0.1236   0.7586   0.0070
  -6.500  -0.1183   0.01475   0.00930  -0.1232   0.7551   0.0071
  -6.250  -0.0941   0.01394   0.00835  -0.1228   0.7517   0.0072
  -6.000  -0.0696   0.01318   0.00745  -0.1224   0.7481   0.0072
  -5.750  -0.0445   0.01256   0.00675  -0.1221   0.7450   0.0073
  -5.500  -0.0194   0.01195   0.00607  -0.1218   0.7418   0.0074
  -5.250   0.0060   0.01142   0.00549  -0.1215   0.7386   0.0076
  -5.000   0.0323   0.01110   0.00510  -0.1214   0.7354   0.0081
  -4.750   0.0584   0.01073   0.00466  -0.1213   0.7320   0.0083
  -4.500   0.0848   0.01037   0.00427  -0.1212   0.7293   0.0085
  -4.250   0.1113   0.00999   0.00385  -0.1211   0.7262   0.0086
  -4.000   0.1374   0.00950   0.00331  -0.1210   0.7231   0.0090
  -3.750   0.1645   0.00923   0.00299  -0.1210   0.7200   0.0099
  -3.500   0.1922   0.00900   0.00270  -0.1211   0.7166   0.0129
  -3.250   0.2191   0.00857   0.00242  -0.1212   0.7139   0.0433
  -3.000   0.2466   0.00831   0.00229  -0.1214   0.7108   0.0752
  -2.750   0.2741   0.00803   0.00216  -0.1217   0.7076   0.1256
  -2.500   0.3011   0.00755   0.00203  -0.1222   0.7042   0.2359
  -2.250   0.3278   0.00660   0.00185  -0.1231   0.7007   0.4863
  -2.000   0.3554   0.00606   0.00185  -0.1235   0.6976   0.6680
  -1.750   0.3840   0.00605   0.00188  -0.1237   0.6943   0.6973
  -1.500   0.4127   0.00609   0.00189  -0.1239   0.6910   0.7127
  -1.250   0.4412   0.00616   0.00192  -0.1241   0.6876   0.7273
  -1.000   0.4702   0.00623   0.00194  -0.1244   0.6845   0.7371
  -0.750   0.4984   0.00626   0.00199  -0.1245   0.6811   0.7444
  -0.500   0.5272   0.00632   0.00200  -0.1248   0.6776   0.7512
  -0.250   0.5552   0.00637   0.00204  -0.1249   0.6739   0.7577
   0.000   0.5833   0.00648   0.00212  -0.1250   0.6700   0.7660
   0.250   0.6108   0.00653   0.00220  -0.1249   0.6659   0.7742
   0.500   0.6386   0.00662   0.00228  -0.1249   0.6617   0.7814
   0.750   0.6668   0.00668   0.00229  -0.1251   0.6576   0.7847
   1.000   0.6949   0.00669   0.00230  -0.1253   0.6535   0.7867
   1.250   0.7230   0.00670   0.00232  -0.1255   0.6491   0.7886
   1.500   0.7508   0.00674   0.00234  -0.1257   0.6443   0.7904
   1.750   0.7786   0.00680   0.00237  -0.1258   0.6395   0.7924
   2.000   0.8067   0.00682   0.00240  -0.1261   0.6342   0.7944
   2.250   0.8343   0.00687   0.00242  -0.1262   0.6289   0.7963
   2.500   0.8621   0.00693   0.00246  -0.1264   0.6237   0.7979
   2.750   0.8898   0.00696   0.00250  -0.1266   0.6177   0.7997
   3.000   0.9164   0.00703   0.00255  -0.1265   0.6118   0.8016
   3.250   0.9439   0.00706   0.00261  -0.1266   0.6055   0.8034
   3.500   0.9704   0.00714   0.00267  -0.1265   0.5986   0.8052
   3.750   0.9973   0.00720   0.00275  -0.1266   0.5917   0.8071
   4.000   1.0234   0.00729   0.00283  -0.1264   0.5837   0.8091
   4.250   1.0499   0.00738   0.00291  -0.1264   0.5753   0.8111
   4.500   1.0751   0.00751   0.00302  -0.1261   0.5661   0.8132
   4.750   1.1009   0.00761   0.00311  -0.1259   0.5560   0.8151
   5.000   1.1257   0.00772   0.00322  -0.1256   0.5452   0.8172
   5.250   1.1497   0.00787   0.00336  -0.1250   0.5336   0.8192
   5.500   1.1730   0.00804   0.00352  -0.1244   0.5208   0.8213
   5.750   1.1957   0.00824   0.00368  -0.1236   0.5062   0.8236
   6.000   1.2178   0.00846   0.00387  -0.1228   0.4903   0.8260
   6.250   1.2388   0.00872   0.00408  -0.1217   0.4723   0.8285
   6.500   1.2578   0.00901   0.00431  -0.1203   0.4520   0.8311
   6.750   1.2746   0.00935   0.00459  -0.1184   0.4323   0.8338
   7.000   1.2905   0.00965   0.00485  -0.1163   0.4136   0.8365
   7.250   1.3038   0.01004   0.00517  -0.1138   0.3919   0.8397
   7.500   1.3165   0.01049   0.00554  -0.1112   0.3701   0.8429
   7.750   1.3290   0.01096   0.00593  -0.1087   0.3481   0.8462
   8.000   1.3397   0.01148   0.00639  -0.1059   0.3272   0.8500
   8.250   1.3509   0.01202   0.00687  -0.1033   0.3050   0.8541
   8.750   1.3705   0.01327   0.00797  -0.0978   0.2642   0.8626
   9.000   1.3777   0.01402   0.00865  -0.0948   0.2420   0.8677
   9.250   1.3849   0.01484   0.00939  -0.0919   0.2208   0.8733
   9.500   1.3889   0.01582   0.01028  -0.0887   0.1970   0.8796
   9.750   1.3965   0.01669   0.01111  -0.0861   0.1798   0.8872
  10.000   1.3995   0.01780   0.01214  -0.0830   0.1570   0.8973
  10.250   1.4034   0.01887   0.01318  -0.0801   0.1395   0.9119
  10.500   1.4074   0.01989   0.01423  -0.0773   0.1221   0.9638
  10.750   1.4158   0.02103   0.01532  -0.0756   0.1086   1.0000
  11.000   1.4230   0.02232   0.01655  -0.0738   0.0946   1.0000
  11.250   1.4301   0.02365   0.01782  -0.0720   0.0821   1.0000
  11.500   1.4360   0.02508   0.01920  -0.0703   0.0697   1.0000
  11.750   1.4429   0.02650   0.02057  -0.0687   0.0598   1.0000
  12.000   1.4497   0.02796   0.02201  -0.0672   0.0511   1.0000
  12.250   1.4553   0.02955   0.02357  -0.0657   0.0427   1.0000
  12.500   1.4609   0.03119   0.02518  -0.0642   0.0357   1.0000
  12.750   1.4666   0.03287   0.02685  -0.0629   0.0296   1.0000
  13.000   1.4738   0.03447   0.02846  -0.0618   0.0252   1.0000
  13.250   1.4798   0.03622   0.03022  -0.0607   0.0211   1.0000
  13.500   1.4858   0.03801   0.03203  -0.0597   0.0181   1.0000
  13.750   1.4920   0.03984   0.03387  -0.0588   0.0151   1.0000
  14.000   1.4983   0.04170   0.03578  -0.0579   0.0132   1.0000
  14.250   1.5028   0.04376   0.03786  -0.0571   0.0108   1.0000
  14.500   1.5092   0.04570   0.03985  -0.0565   0.0095   1.0000
  14.750   1.5135   0.04791   0.04211  -0.0558   0.0080   1.0000
  15.000   1.5168   0.05027   0.04450  -0.0552   0.0060   1.0000
  15.250   1.5222   0.05247   0.04677  -0.0548   0.0054   1.0000
  15.500   1.5219   0.05535   0.04969  -0.0544   0.0035   1.0000
  15.750   1.5220   0.05826   0.05267  -0.0540   0.0024   1.0000
  16.000   1.5182   0.06176   0.05625  -0.0537   0.0014   1.0000
  16.250   1.5211   0.06450   0.05907  -0.0537   0.0014   1.0000
  16.500   1.5153   0.06841   0.06309  -0.0538   0.0010   1.0000
  16.750   1.5157   0.07164   0.06641  -0.0540   0.0009   1.0000
  17.000   1.5150   0.07508   0.06995  -0.0544   0.0008   1.0000
  17.250   1.5143   0.07860   0.07358  -0.0549   0.0008   1.0000
  17.500   1.5122   0.08237   0.07745  -0.0556   0.0007   1.0000
  17.750   1.5081   0.08651   0.08171  -0.0564   0.0007   1.0000
  18.000   1.5066   0.09037   0.08566  -0.0574   0.0007   1.0000
  18.250   1.5006   0.09499   0.09040  -0.0586   0.0006   1.0000
  18.500   1.4950   0.09964   0.09516  -0.0600   0.0006   1.0000
  18.750   1.4870   0.10474   0.10037  -0.0617   0.0006   1.0000
  19.000   1.4807   0.10966   0.10541  -0.0635   0.0006   1.0000
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