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EPPLER 587 AIRFOIL (e587-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 587 AIRFOIL (e587-il)
Reynolds number: 100,000
Max Cl/Cd: 41.91 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e587-il-100000-n5.txt
Download as CSV file: xf-e587-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 587 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1995   0.09782   0.09284  -0.0968   0.9473   0.0224
 -10.500  -0.2211   0.08414   0.07917  -0.1057   0.9416   0.0205
 -10.250  -0.2240   0.07704   0.07205  -0.1113   0.9353   0.0203
 -10.000  -0.2314   0.06904   0.06394  -0.1194   0.9309   0.0200
  -9.750  -0.2487   0.06308   0.05784  -0.1239   0.9212   0.0197
  -9.500  -0.2589   0.05727   0.05179  -0.1296   0.9155   0.0195
  -9.250  -0.2761   0.05385   0.04818  -0.1299   0.9042   0.0194
  -9.000  -0.2893   0.05061   0.04468  -0.1298   0.8950   0.0193
  -8.750  -0.2949   0.04731   0.04105  -0.1297   0.8871   0.0192
  -8.500  -0.2978   0.04422   0.03758  -0.1286   0.8799   0.0192
  -8.250  -0.2953   0.04154   0.03454  -0.1273   0.8728   0.0193
  -8.000  -0.2799   0.03830   0.03079  -0.1278   0.8691   0.0195
  -7.750  -0.2749   0.03645   0.02861  -0.1253   0.8616   0.0197
  -7.500  -0.2572   0.03429   0.02605  -0.1246   0.8570   0.0201
  -7.250  -0.2312   0.03217   0.02359  -0.1251   0.8542   0.0208
  -7.000  -0.2014   0.03082   0.02211  -0.1265   0.8520   0.0222
  -6.750  -0.1958   0.03022   0.02139  -0.1230   0.8439   0.0233
  -6.500  -0.1709   0.02898   0.01997  -0.1229   0.8404   0.0255
  -6.250  -0.1423   0.02782   0.01871  -0.1235   0.8379   0.0274
  -6.000  -0.1120   0.02655   0.01728  -0.1242   0.8359   0.0297
  -5.750  -0.1095   0.02627   0.01704  -0.1202   0.8275   0.0314
  -5.500  -0.0850   0.02546   0.01616  -0.1202   0.8241   0.0365
  -5.250  -0.0568   0.02455   0.01521  -0.1209   0.8216   0.0435
  -5.000  -0.0352   0.02389   0.01456  -0.1204   0.8177   0.0544
  -4.750  -0.0241   0.02355   0.01424  -0.1179   0.8111   0.0685
  -4.500   0.0016   0.02270   0.01360  -0.1183   0.8078   0.1021
  -4.250   0.0310   0.02160   0.01290  -0.1198   0.8054   0.1820
  -4.000   0.0598   0.01992   0.01228  -0.1221   0.8032   0.3983
  -3.750   0.0599   0.02050   0.01349  -0.1163   0.7952   0.5302
  -3.500   0.0885   0.02088   0.01375  -0.1160   0.7920   0.5966
  -3.250   0.1199   0.02125   0.01393  -0.1160   0.7896   0.6300
  -3.000   0.1505   0.02164   0.01417  -0.1156   0.7877   0.6509
  -2.750   0.1541   0.02231   0.01480  -0.1113   0.7794   0.6647
  -2.500   0.1769   0.02275   0.01513  -0.1095   0.7759   0.6817
  -2.250   0.2025   0.02312   0.01540  -0.1080   0.7734   0.6985
  -2.000   0.2350   0.02323   0.01535  -0.1084   0.7716   0.7124
  -1.750   0.2307   0.02388   0.01603  -0.1025   0.7627   0.7177
  -1.500   0.2594   0.02386   0.01587  -0.1028   0.7596   0.7241
  -1.250   0.2959   0.02367   0.01551  -0.1049   0.7574   0.7298
  -1.000   0.3300   0.02351   0.01523  -0.1060   0.7556   0.7329
  -0.750   0.3287   0.02411   0.01584  -0.1014   0.7466   0.7373
  -0.500   0.3608   0.02402   0.01564  -0.1027   0.7435   0.7415
  -0.250   0.3989   0.02383   0.01531  -0.1051   0.7413   0.7456
   0.000   0.4344   0.02364   0.01503  -0.1065   0.7395   0.7479
   0.250   0.4299   0.02435   0.01578  -0.1015   0.7300   0.7515
   0.500   0.4624   0.02426   0.01561  -0.1026   0.7270   0.7549
   0.750   0.5007   0.02408   0.01535  -0.1049   0.7249   0.7582
   1.000   0.5314   0.02411   0.01531  -0.1061   0.7212   0.7617
   1.250   0.5325   0.02467   0.01592  -0.1018   0.7128   0.7648
   1.500   0.5663   0.02453   0.01574  -0.1030   0.7100   0.7676
   1.750   0.6057   0.02429   0.01546  -0.1053   0.7080   0.7703
   2.250   0.6384   0.02498   0.01615  -0.1027   0.6951   0.7779
   2.500   0.6744   0.02472   0.01588  -0.1041   0.6927   0.7803
   3.000   0.7040   0.02542   0.01666  -0.1005   0.6796   0.7869
   3.250   0.7433   0.02510   0.01632  -0.1026   0.6770   0.7899
   3.750   0.7768   0.02580   0.01711  -0.0998   0.6637   0.7972
   4.000   0.8153   0.02536   0.01670  -0.1015   0.6609   0.8002
   4.500   0.8520   0.02602   0.01745  -0.0994   0.6471   0.8077
   4.750   0.8940   0.02547   0.01695  -0.1017   0.6444   0.8109
   5.250   0.9276   0.02604   0.01766  -0.0986   0.6299   0.8191
   5.500   0.9347   0.02686   0.01858  -0.0961   0.6202   0.8239
   5.750   0.9680   0.02650   0.01827  -0.0970   0.6152   0.8275
   6.250   1.0086   0.02679   0.01873  -0.0950   0.5998   0.8363
   6.500   1.0263   0.02716   0.01918  -0.0939   0.5911   0.8418
   6.750   1.0513   0.02699   0.01910  -0.0934   0.5837   0.8465
   7.000   1.0630   0.02757   0.01978  -0.0915   0.5737   0.8523
   7.250   1.0977   0.02709   0.01938  -0.0924   0.5667   0.8575
   7.500   1.1032   0.02787   0.02028  -0.0896   0.5550   0.8638
   7.750   1.1266   0.02787   0.02037  -0.0890   0.5455   0.8708
   8.000   1.1486   0.02783   0.02043  -0.0881   0.5354   0.8782
   8.250   1.1589   0.02849   0.02119  -0.0861   0.5226   0.8876
   8.500   1.1734   0.02881   0.02161  -0.0844   0.5105   0.8979
   8.750   1.1923   0.02892   0.02182  -0.0832   0.4980   0.9107
   9.000   1.2108   0.02901   0.02199  -0.0819   0.4849   0.9306
   9.250   1.2263   0.02926   0.02230  -0.0806   0.4703   1.0000
   9.500   1.2451   0.02994   0.02300  -0.0802   0.4544   1.0000
   9.750   1.2611   0.03078   0.02387  -0.0796   0.4376   1.0000
  10.000   1.2757   0.03171   0.02483  -0.0788   0.4205   1.0000
  10.250   1.2890   0.03273   0.02585  -0.0778   0.4030   1.0000
  10.500   1.3009   0.03386   0.02697  -0.0767   0.3852   1.0000
  10.750   1.3114   0.03509   0.02821  -0.0756   0.3675   1.0000
  11.000   1.3206   0.03643   0.02954  -0.0744   0.3498   1.0000
  11.250   1.3286   0.03790   0.03099  -0.0731   0.3324   1.0000
  11.500   1.3349   0.03951   0.03258  -0.0718   0.3152   1.0000
  11.750   1.3403   0.04125   0.03430  -0.0705   0.2983   1.0000
  12.000   1.3446   0.04313   0.03619  -0.0692   0.2816   1.0000
  12.250   1.3481   0.04515   0.03821  -0.0680   0.2653   1.0000
  12.500   1.3510   0.04728   0.04035  -0.0669   0.2495   1.0000
  12.750   1.3534   0.04953   0.04262  -0.0659   0.2342   1.0000
  13.000   1.3550   0.05193   0.04502  -0.0650   0.2193   1.0000
  13.250   1.3560   0.05445   0.04755  -0.0641   0.2050   1.0000
  13.500   1.3564   0.05712   0.05025  -0.0634   0.1911   1.0000
  13.750   1.3567   0.05991   0.05308  -0.0629   0.1775   1.0000
  14.000   1.3567   0.06281   0.05603  -0.0624   0.1645   1.0000
  14.250   1.3561   0.06586   0.05912  -0.0621   0.1521   1.0000
  14.500   1.3550   0.06905   0.06235  -0.0619   0.1405   1.0000
  14.750   1.3528   0.07246   0.06580  -0.0619   0.1297   1.0000
  15.000   1.3492   0.07612   0.06946  -0.0620   0.1199   1.0000
  15.250   1.3475   0.07966   0.07310  -0.0622   0.1097   1.0000
  15.500   1.3450   0.08339   0.07693  -0.0626   0.1009   1.0000
  15.750   1.3402   0.08749   0.08105  -0.0632   0.0932   1.0000
  16.000   1.3372   0.09147   0.08513  -0.0639   0.0853   1.0000
  16.250   1.3332   0.09563   0.08936  -0.0648   0.0786   1.0000
  16.500   1.3277   0.10009   0.09389  -0.0659   0.0725   1.0000
  16.750   1.3241   0.10435   0.09826  -0.0671   0.0667   1.0000
  17.000   1.3180   0.10906   0.10302  -0.0686   0.0619   1.0000
  17.250   1.3144   0.11344   0.10751  -0.0700   0.0571   1.0000
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