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EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 598 AIRFOIL (e598-il)
Reynolds number: 200,000
Max Cl/Cd: 75.56 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e598-il-200000-n5.txt
Download as CSV file: xf-e598-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 598 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3489   0.09263   0.08846  -0.0103   0.6765   0.0125
  -8.500  -0.3456   0.08915   0.08496  -0.0120   0.6687   0.0124
  -8.250  -0.3433   0.08559   0.08139  -0.0137   0.6614   0.0122
  -8.000  -0.3430   0.08175   0.07755  -0.0156   0.6545   0.0121
  -7.000  -0.4119   0.03358   0.02830  -0.0460   0.6428   0.0102
  -6.750  -0.3968   0.02894   0.02301  -0.0467   0.6367   0.0104
  -6.500  -0.3764   0.02637   0.01998  -0.0467   0.6309   0.0106
  -6.250  -0.3537   0.02437   0.01760  -0.0465   0.6242   0.0110
  -6.000  -0.3302   0.02266   0.01549  -0.0461   0.6181   0.0114
  -5.750  -0.3056   0.02116   0.01364  -0.0457   0.6122   0.0119
  -5.500  -0.2802   0.01990   0.01204  -0.0452   0.6061   0.0126
  -5.250  -0.2544   0.01908   0.01107  -0.0450   0.6009   0.0134
  -5.000  -0.2279   0.01836   0.01015  -0.0447   0.5956   0.0150
  -4.750  -0.2011   0.01775   0.00943  -0.0445   0.5898   0.0171
  -4.500  -0.1744   0.01707   0.00857  -0.0441   0.5848   0.0193
  -4.250  -0.1475   0.01643   0.00778  -0.0438   0.5802   0.0225
  -4.000  -0.1203   0.01591   0.00722  -0.0436   0.5751   0.0274
  -3.750  -0.0929   0.01551   0.00674  -0.0433   0.5702   0.0350
  -3.500  -0.0656   0.01520   0.00635  -0.0431   0.5660   0.0434
  -3.250  -0.0378   0.01495   0.00609  -0.0430   0.5611   0.0528
  -3.000  -0.0100   0.01472   0.00581  -0.0428   0.5565   0.0621
  -2.750   0.0175   0.01450   0.00552  -0.0426   0.5522   0.0709
  -2.500   0.0451   0.01429   0.00524  -0.0424   0.5483   0.0797
  -2.250   0.0731   0.01411   0.00502  -0.0422   0.5436   0.0893
  -2.000   0.1008   0.01393   0.00482  -0.0421   0.5394   0.0995
  -1.750   0.1284   0.01376   0.00462  -0.0419   0.5354   0.1101
  -1.500   0.1560   0.01362   0.00444  -0.0417   0.5316   0.1216
  -1.250   0.1838   0.01348   0.00430  -0.0416   0.5272   0.1346
  -1.000   0.2116   0.01335   0.00417  -0.0414   0.5230   0.1496
  -0.750   0.2391   0.01323   0.00404  -0.0412   0.5192   0.1675
  -0.500   0.2665   0.01311   0.00395  -0.0411   0.5156   0.1908
  -0.250   0.2941   0.01296   0.00391  -0.0410   0.5113   0.2229
   0.000   0.3213   0.01279   0.00387  -0.0408   0.5071   0.2713
   0.250   0.3475   0.01248   0.00381  -0.0406   0.5034   0.3609
   0.500   0.4124   0.01087   0.00379  -0.0476   0.4989   0.9995
   0.750   0.4395   0.01096   0.00380  -0.0473   0.4945   1.0000
   1.000   0.4660   0.01105   0.00380  -0.0469   0.4903   1.0000
   1.250   0.4924   0.01116   0.00379  -0.0465   0.4866   1.0000
   1.500   0.5189   0.01129   0.00381  -0.0461   0.4830   1.0000
   1.750   0.5455   0.01140   0.00389  -0.0458   0.4784   1.0000
   2.000   0.5721   0.01151   0.00394  -0.0455   0.4742   1.0000
   2.250   0.5987   0.01163   0.00398  -0.0451   0.4704   1.0000
   2.500   0.6252   0.01177   0.00406  -0.0448   0.4666   1.0000
   2.750   0.6520   0.01190   0.00418  -0.0446   0.4619   1.0000
   3.000   0.6786   0.01203   0.00428  -0.0443   0.4575   1.0000
   3.250   0.7051   0.01217   0.00435  -0.0440   0.4537   1.0000
   3.500   0.7318   0.01232   0.00450  -0.0437   0.4493   1.0000
   3.750   0.7584   0.01246   0.00465  -0.0435   0.4444   1.0000
   4.000   0.7850   0.01260   0.00478  -0.0432   0.4400   1.0000
   4.250   0.8115   0.01276   0.00489  -0.0429   0.4360   1.0000
   4.500   0.8381   0.01292   0.00511  -0.0427   0.4307   1.0000
   4.750   0.8646   0.01308   0.00528  -0.0425   0.4258   1.0000
   5.000   0.8909   0.01324   0.00540  -0.0422   0.4216   1.0000
   5.250   0.9173   0.01343   0.00565  -0.0420   0.4160   1.0000
   5.500   0.9436   0.01360   0.00585  -0.0418   0.4107   1.0000
   5.750   0.9697   0.01378   0.00601  -0.0415   0.4061   1.0000
   6.000   0.9958   0.01398   0.00630  -0.0413   0.4000   1.0000
   6.250   1.0218   0.01418   0.00652  -0.0410   0.3944   1.0000
   6.500   1.0476   0.01439   0.00676  -0.0408   0.3891   1.0000
   6.750   1.0733   0.01461   0.00706  -0.0405   0.3824   1.0000
   7.000   1.0987   0.01483   0.00729  -0.0402   0.3765   1.0000
   7.250   1.1241   0.01508   0.00763  -0.0399   0.3694   1.0000
   7.500   1.1491   0.01532   0.00789  -0.0396   0.3623   1.0000
   7.750   1.1739   0.01559   0.00825  -0.0393   0.3546   1.0000
   8.000   1.1982   0.01587   0.00855  -0.0389   0.3467   1.0000
   8.250   1.2225   0.01618   0.00894  -0.0385   0.3381   1.0000
   8.500   1.2460   0.01651   0.00930  -0.0381   0.3298   1.0000
   8.750   1.2694   0.01686   0.00974  -0.0377   0.3203   1.0000
   9.000   1.2921   0.01725   0.01019  -0.0371   0.3109   1.0000
   9.500   1.3351   0.01815   0.01119  -0.0359   0.2895   1.0000
   9.750   1.3553   0.01867   0.01177  -0.0352   0.2778   1.0000
  10.000   1.3743   0.01925   0.01239  -0.0344   0.2660   1.0000
  10.250   1.3915   0.01992   0.01310  -0.0334   0.2534   1.0000
  10.500   1.4067   0.02068   0.01388  -0.0322   0.2403   1.0000
  10.750   1.4193   0.02156   0.01478  -0.0308   0.2266   1.0000
  11.000   1.4286   0.02256   0.01580  -0.0292   0.2130   1.0000
  11.250   1.4322   0.02369   0.01696  -0.0269   0.2004   1.0000
  11.500   1.4323   0.02513   0.01843  -0.0248   0.1886   1.0000
  11.750   1.4313   0.02697   0.02030  -0.0234   0.1771   1.0000
  12.000   1.4290   0.02919   0.02253  -0.0225   0.1657   1.0000
  12.250   1.4256   0.03171   0.02507  -0.0220   0.1552   1.0000
  12.500   1.4214   0.03446   0.02783  -0.0217   0.1450   1.0000
  12.750   1.4181   0.03723   0.03064  -0.0215   0.1354   1.0000
  13.000   1.4131   0.04024   0.03368  -0.0214   0.1270   1.0000
  13.250   1.4068   0.04347   0.03694  -0.0214   0.1192   1.0000
  13.500   1.4025   0.04654   0.04007  -0.0216   0.1116   1.0000
  13.750   1.3948   0.05006   0.04361  -0.0218   0.1051   1.0000
  14.000   1.3904   0.05329   0.04690  -0.0221   0.0984   1.0000
  14.250   1.3831   0.05692   0.05057  -0.0226   0.0927   1.0000
  14.500   1.3787   0.06039   0.05410  -0.0232   0.0867   1.0000
  14.750   1.3719   0.06428   0.05804  -0.0240   0.0815   1.0000
  15.000   1.3680   0.06792   0.06174  -0.0248   0.0759   1.0000
  15.250   1.3610   0.07207   0.06593  -0.0259   0.0715   1.0000
  15.500   1.3575   0.07583   0.06979  -0.0269   0.0667   1.0000
  15.750   1.3497   0.08029   0.07428  -0.0283   0.0626   1.0000
  16.000   1.3468   0.08412   0.07821  -0.0294   0.0586   1.0000
  16.250   1.3405   0.08854   0.08269  -0.0308   0.0550   1.0000
  16.500   1.3353   0.09288   0.08711  -0.0323   0.0518   1.0000
  16.750   1.3306   0.09722   0.09153  -0.0338   0.0486   1.0000
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