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EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 582 AIRFOIL (e582-il)
Reynolds number: 1,000,000
Max Cl/Cd: 140.43 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e582-il-1000000.txt
Download as CSV file: xf-e582-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 582 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  -0.0490   0.08278   0.08075  -0.1257   0.9083   0.0082
 -10.250  -0.0416   0.07793   0.07574  -0.1300   0.8817   0.0085
 -10.000  -0.0414   0.07417   0.07188  -0.1316   0.8607   0.0085
  -9.750  -0.0503   0.06765   0.06530  -0.1343   0.8444   0.0088
  -9.500  -0.0539   0.06355   0.06115  -0.1362   0.8320   0.0088
  -9.250  -0.0681   0.05563   0.05318  -0.1422   0.8199   0.0089
  -9.000  -0.0627   0.03455   0.03202  -0.1357   0.7940   0.0089
  -8.750  -0.1028   0.04571   0.04303  -0.1443   0.8007   0.0088
  -8.250  -0.1406   0.03911   0.03610  -0.1382   0.7858   0.0089
  -8.000  -0.1519   0.03576   0.03248  -0.1351   0.7798   0.0089
  -7.750  -0.1729   0.03050   0.02691  -0.1314   0.7745   0.0092
  -7.500  -0.1624   0.02883   0.02513  -0.1301   0.7701   0.0093
  -7.250  -0.1505   0.02717   0.02330  -0.1287   0.7659   0.0094
  -7.000  -0.1636   0.01808   0.01316  -0.1225   0.7616   0.0055
  -6.750  -0.1462   0.01556   0.01023  -0.1209   0.7581   0.0054
  -6.500  -0.1233   0.01453   0.00902  -0.1202   0.7547   0.0056
  -6.250  -0.0991   0.01381   0.00815  -0.1197   0.7513   0.0060
  -6.000  -0.0740   0.01330   0.00750  -0.1194   0.7478   0.0063
  -5.750  -0.0494   0.01264   0.00673  -0.1189   0.7449   0.0066
  -5.500  -0.0264   0.01178   0.00581  -0.1183   0.7417   0.0069
  -5.250  -0.0016   0.01129   0.00527  -0.1180   0.7385   0.0071
  -5.000   0.0239   0.01093   0.00486  -0.1178   0.7353   0.0074
  -4.750   0.0498   0.01061   0.00448  -0.1176   0.7319   0.0076
  -4.500   0.0757   0.01025   0.00409  -0.1174   0.7293   0.0079
  -4.250   0.1021   0.00996   0.00378  -0.1173   0.7263   0.0083
  -4.000   0.1292   0.00978   0.00356  -0.1173   0.7232   0.0089
  -3.750   0.1551   0.00940   0.00313  -0.1172   0.7201   0.0099
  -3.500   0.1825   0.00922   0.00289  -0.1172   0.7167   0.0110
  -3.250   0.2091   0.00886   0.00256  -0.1171   0.7141   0.0205
  -3.000   0.2354   0.00847   0.00238  -0.1172   0.7110   0.0651
  -2.750   0.2625   0.00821   0.00226  -0.1174   0.7080   0.1066
  -2.500   0.2893   0.00788   0.00215  -0.1176   0.7048   0.1804
  -2.250   0.3154   0.00720   0.00202  -0.1181   0.7013   0.3626
  -2.000   0.3411   0.00600   0.00194  -0.1188   0.6986   0.7007
  -1.750   0.3694   0.00606   0.00204  -0.1189   0.6953   0.7435
  -1.500   0.3980   0.00613   0.00207  -0.1191   0.6921   0.7577
  -1.250   0.4268   0.00625   0.00213  -0.1193   0.6888   0.7699
  -1.000   0.4548   0.00639   0.00224  -0.1193   0.6854   0.7782
  -0.750   0.4833   0.00646   0.00228  -0.1195   0.6822   0.7850
  -0.500   0.5109   0.00651   0.00234  -0.1194   0.6786   0.7897
  -0.250   0.5386   0.00660   0.00240  -0.1194   0.6748   0.7951
   0.000   0.5666   0.00674   0.00248  -0.1195   0.6708   0.8016
   0.250   0.5923   0.00686   0.00266  -0.1189   0.6670   0.8094
   0.500   0.6194   0.00698   0.00277  -0.1187   0.6628   0.8169
   0.750   0.6456   0.00705   0.00283  -0.1183   0.6588   0.8206
   1.000   0.6734   0.00710   0.00286  -0.1185   0.6548   0.8224
   1.250   0.7015   0.00711   0.00287  -0.1187   0.6505   0.8239
   1.500   0.7295   0.00713   0.00286  -0.1189   0.6458   0.8251
   1.750   0.7573   0.00718   0.00287  -0.1191   0.6408   0.8262
   2.000   0.7855   0.00718   0.00288  -0.1194   0.6358   0.8272
   2.250   0.8132   0.00722   0.00289  -0.1196   0.6302   0.8282
   2.500   0.8407   0.00727   0.00291  -0.1198   0.6250   0.8289
   2.750   0.8687   0.00729   0.00294  -0.1201   0.6191   0.8297
   3.000   0.8958   0.00736   0.00297  -0.1202   0.6132   0.8304
   3.250   0.9232   0.00738   0.00301  -0.1203   0.6071   0.8312
   3.500   0.9499   0.00742   0.00303  -0.1203   0.6002   0.8319
   3.750   0.9763   0.00748   0.00308  -0.1203   0.5935   0.8327
   4.000   1.0026   0.00753   0.00314  -0.1202   0.5858   0.8334
   4.250   1.0284   0.00761   0.00321  -0.1201   0.5778   0.8341
   4.500   1.0536   0.00771   0.00329  -0.1198   0.5687   0.8350
   4.750   1.0792   0.00780   0.00339  -0.1196   0.5596   0.8360
   5.000   1.1035   0.00793   0.00350  -0.1191   0.5495   0.8368
   5.250   1.1275   0.00806   0.00361  -0.1187   0.5381   0.8376
   5.500   1.1515   0.00820   0.00374  -0.1182   0.5259   0.8384
   5.750   1.1742   0.00837   0.00389  -0.1175   0.5123   0.8393
   6.000   1.1959   0.00857   0.00405  -0.1165   0.4972   0.8402
   6.250   1.2165   0.00880   0.00424  -0.1154   0.4811   0.8412
   6.500   1.2344   0.00909   0.00446  -0.1138   0.4625   0.8422
   6.750   1.2506   0.00937   0.00468  -0.1118   0.4432   0.8433
   7.000   1.2653   0.00971   0.00495  -0.1095   0.4228   0.8444
   7.250   1.2798   0.01010   0.00527  -0.1072   0.4034   0.8455
   7.500   1.2931   0.01051   0.00561  -0.1048   0.3818   0.8468
   7.750   1.3057   0.01097   0.00599  -0.1023   0.3603   0.8481
   8.000   1.3172   0.01147   0.00642  -0.0997   0.3401   0.8494
   8.250   1.3287   0.01200   0.00688  -0.0972   0.3185   0.8508
   8.500   1.3377   0.01264   0.00743  -0.0943   0.2968   0.8522
   8.750   1.3481   0.01326   0.00798  -0.0917   0.2764   0.8537
   9.000   1.3557   0.01402   0.00865  -0.0888   0.2544   0.8553
   9.250   1.3617   0.01490   0.00942  -0.0858   0.2299   0.8570
   9.500   1.3664   0.01590   0.01029  -0.0828   0.2058   0.8587
   9.750   1.3738   0.01683   0.01115  -0.0803   0.1865   0.8601
  10.000   1.3848   0.01761   0.01192  -0.0784   0.1756   0.8618
  10.250   1.3873   0.01886   0.01305  -0.0754   0.1527   0.8641
  10.500   1.3933   0.01999   0.01412  -0.0731   0.1354   0.8663
  10.750   1.3961   0.02138   0.01541  -0.0705   0.1149   0.8685
  11.000   1.4038   0.02253   0.01653  -0.0686   0.1030   0.8706
  11.250   1.4098   0.02385   0.01781  -0.0667   0.0898   0.8728
  11.500   1.4160   0.02521   0.01912  -0.0649   0.0779   0.8749
  11.750   1.4205   0.02670   0.02056  -0.0630   0.0655   0.8774
  12.000   1.4276   0.02805   0.02192  -0.0614   0.0569   0.8801
  12.250   1.4324   0.02962   0.02347  -0.0597   0.0472   0.8831
  12.500   1.4373   0.03124   0.02507  -0.0582   0.0389   0.8863
  12.750   1.4434   0.03284   0.02666  -0.0569   0.0328   0.8895
  13.000   1.4487   0.03451   0.02835  -0.0556   0.0273   0.8934
  13.250   1.4542   0.03619   0.03006  -0.0543   0.0232   0.8982
  13.500   1.4613   0.03780   0.03173  -0.0533   0.0201   0.9037
  13.750   1.4663   0.03957   0.03354  -0.0521   0.0172   0.9114
  14.000   1.4708   0.04134   0.03539  -0.0509   0.0146   0.9244
  14.250   1.4765   0.04309   0.03726  -0.0501   0.0124   1.0000
  14.500   1.4828   0.04507   0.03928  -0.0496   0.0109   1.0000
  14.750   1.4887   0.04713   0.04138  -0.0491   0.0092   1.0000
  15.000   1.4933   0.04937   0.04366  -0.0486   0.0078   1.0000
  15.250   1.4958   0.05188   0.04619  -0.0482   0.0053   1.0000
  15.500   1.4961   0.05467   0.04903  -0.0477   0.0034   1.0000
  15.750   1.4964   0.05757   0.05199  -0.0474   0.0023   1.0000
  16.000   1.4942   0.06083   0.05533  -0.0472   0.0014   1.0000
  16.250   1.4902   0.06443   0.05903  -0.0471   0.0009   1.0000
  16.500   1.4911   0.06748   0.06217  -0.0472   0.0008   1.0000
  16.750   1.4922   0.07059   0.06536  -0.0475   0.0007   1.0000
  17.000   1.4911   0.07405   0.06893  -0.0479   0.0007   1.0000
  17.250   1.4915   0.07740   0.07237  -0.0484   0.0006   1.0000
  17.500   1.4892   0.08116   0.07623  -0.0491   0.0006   1.0000
  17.750   1.4875   0.08492   0.08009  -0.0498   0.0006   1.0000
  18.000   1.4814   0.08943   0.08472  -0.0509   0.0005   1.0000
  18.250   1.4761   0.09390   0.08931  -0.0521   0.0005   1.0000
  18.500   1.4680   0.09893   0.09446  -0.0536   0.0005   1.0000
  18.750   1.4598   0.10405   0.09971  -0.0553   0.0005   1.0000
  19.000   1.4508   0.10942   0.10520  -0.0573   0.0004   1.0000
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