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EPPLER 551 AIRFOIL (e551-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 551 AIRFOIL (e551-il)
Reynolds number: 500,000
Max Cl/Cd: 102.43 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e551-il-500000.txt
Download as CSV file: xf-e551-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 551 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.4109   0.12351   0.12108  -0.0531   1.0000   0.0095
 -16.500  -0.5269   0.12720   0.12455  -0.0474   1.0000   0.0093
 -16.250  -0.5510   0.11742   0.11472  -0.0518   1.0000   0.0091
 -16.000  -0.5770   0.10718   0.10437  -0.0572   1.0000   0.0089
 -15.750  -0.5992   0.09845   0.09551  -0.0619   1.0000   0.0088
 -15.500  -0.6243   0.08979   0.08669  -0.0666   1.0000   0.0086
 -15.250  -0.6498   0.08173   0.07844  -0.0708   1.0000   0.0086
 -15.000  -0.6707   0.07506   0.07159  -0.0740   1.0000   0.0084
 -14.750  -0.6873   0.06948   0.06584  -0.0764   1.0000   0.0083
 -14.500  -0.7079   0.06367   0.05981  -0.0785   1.0000   0.0083
 -14.250  -0.7218   0.05909   0.05505  -0.0797   1.0000   0.0081
 -14.000  -0.7318   0.05530   0.05109  -0.0805   1.0000   0.0081
 -13.750  -0.7426   0.05158   0.04715  -0.0807   1.0000   0.0079
 -13.500  -0.7457   0.04895   0.04442  -0.0807   1.0000   0.0081
 -13.250  -0.7491   0.04632   0.04165  -0.0803   1.0000   0.0081
 -13.000  -0.7504   0.04402   0.03923  -0.0797   1.0000   0.0080
 -12.750  -0.7504   0.04196   0.03706  -0.0788   1.0000   0.0080
 -12.500  -0.7498   0.04014   0.03517  -0.0778   1.0000   0.0082
 -12.250  -0.7492   0.03846   0.03342  -0.0763   1.0000   0.0083
 -12.000  -0.7497   0.03697   0.03187  -0.0745   1.0000   0.0083
 -11.750  -0.7446   0.03544   0.03027  -0.0738   0.9993   0.0085
 -11.500  -0.7183   0.03350   0.02820  -0.0769   0.9958   0.0088
 -11.250  -0.6931   0.03172   0.02633  -0.0795   0.9899   0.0090
 -11.000  -0.6675   0.03007   0.02457  -0.0822   0.9816   0.0093
 -10.750  -0.6512   0.02809   0.02255  -0.0835   0.9669   0.0097
 -10.500  -0.6249   0.02630   0.02073  -0.0868   0.9574   0.0101
 -10.250  -0.5923   0.02456   0.01893  -0.0912   0.9481   0.0103
 -10.000  -0.5502   0.02295   0.01722  -0.0972   0.9411   0.0114
  -9.750  -0.5118   0.02099   0.01515  -0.1034   0.9270   0.0121
  -9.500  -0.4826   0.01938   0.01342  -0.1074   0.9075   0.0128
  -9.250  -0.4691   0.01824   0.01215  -0.1074   0.8862   0.0137
  -9.000  -0.4666   0.01732   0.01107  -0.1051   0.8669   0.0148
  -8.750  -0.4599   0.01657   0.01022  -0.1028   0.8522   0.0156
  -8.500  -0.4455   0.01603   0.00958  -0.1013   0.8404   0.0179
  -8.250  -0.4319   0.01540   0.00889  -0.0997   0.8287   0.0204
  -8.000  -0.4162   0.01480   0.00824  -0.0984   0.8184   0.0255
  -7.750  -0.4000   0.01413   0.00755  -0.0971   0.8090   0.0338
  -7.500  -0.3822   0.01351   0.00697  -0.0961   0.7995   0.0476
  -7.250  -0.3631   0.01289   0.00640  -0.0952   0.7911   0.0699
  -7.000  -0.3436   0.01224   0.00588  -0.0945   0.7822   0.1007
  -6.750  -0.3237   0.01153   0.00532  -0.0939   0.7744   0.1478
  -6.500  -0.3061   0.01046   0.00461  -0.0932   0.7660   0.2308
  -6.250  -0.2883   0.00933   0.00402  -0.0926   0.7588   0.3678
  -6.000  -0.2617   0.00925   0.00399  -0.0925   0.7511   0.4103
  -5.750  -0.2339   0.00930   0.00395  -0.0925   0.7438   0.4292
  -5.500  -0.2059   0.00938   0.00395  -0.0925   0.7365   0.4426
  -5.250  -0.1781   0.00943   0.00395  -0.0925   0.7293   0.4516
  -5.000  -0.1497   0.00955   0.00392  -0.0926   0.7228   0.4600
  -4.750  -0.1218   0.00957   0.00394  -0.0926   0.7157   0.4669
  -4.500  -0.0935   0.00968   0.00393  -0.0926   0.7094   0.4738
  -4.250  -0.0656   0.00970   0.00390  -0.0927   0.7024   0.4796
  -4.000  -0.0375   0.00987   0.00405  -0.0926   0.6957   0.4883
  -3.750  -0.0095   0.01000   0.00409  -0.0926   0.6895   0.4961
  -3.500   0.0187   0.00997   0.00406  -0.0927   0.6830   0.4993
  -3.250   0.0470   0.00997   0.00397  -0.0928   0.6771   0.5017
  -3.000   0.0753   0.00995   0.00389  -0.0930   0.6710   0.5040
  -2.750   0.1036   0.00992   0.00379  -0.0931   0.6646   0.5062
  -2.500   0.1320   0.00995   0.00370  -0.0934   0.6590   0.5084
  -2.250   0.1603   0.00991   0.00363  -0.0935   0.6530   0.5104
  -2.000   0.1884   0.00983   0.00351  -0.0937   0.6474   0.5126
  -1.750   0.2168   0.00983   0.00346  -0.0939   0.6421   0.5145
  -1.500   0.2449   0.00980   0.00343  -0.0940   0.6364   0.5166
  -1.250   0.2730   0.00980   0.00339  -0.0941   0.6308   0.5188
  -1.000   0.3015   0.00985   0.00337  -0.0943   0.6258   0.5213
  -0.750   0.3297   0.00984   0.00336  -0.0945   0.6206   0.5238
  -0.500   0.3580   0.00987   0.00333  -0.0947   0.6154   0.5260
  -0.250   0.3863   0.00989   0.00329  -0.0949   0.6106   0.5281
   0.000   0.4142   0.00986   0.00329  -0.0950   0.6056   0.5304
   0.250   0.4423   0.00986   0.00330  -0.0951   0.6006   0.5328
   0.500   0.4705   0.00991   0.00332  -0.0953   0.5961   0.5352
   0.750   0.4987   0.00997   0.00336  -0.0955   0.5916   0.5380
   1.000   0.5266   0.00999   0.00339  -0.0956   0.5868   0.5409
   1.250   0.5548   0.01005   0.00342  -0.0958   0.5822   0.5435
   1.500   0.5829   0.01009   0.00344  -0.0960   0.5779   0.5463
   1.750   0.6106   0.01010   0.00350  -0.0960   0.5735   0.5491
   2.000   0.6383   0.01013   0.00356  -0.0961   0.5689   0.5520
   2.250   0.6661   0.01020   0.00362  -0.0962   0.5646   0.5551
   2.500   0.6944   0.01031   0.00370  -0.0965   0.5603   0.5583
   2.750   0.7217   0.01035   0.00377  -0.0965   0.5559   0.5615
   3.000   0.7489   0.01036   0.00384  -0.0965   0.5512   0.5651
   3.250   0.7765   0.01044   0.00392  -0.0965   0.5468   0.5688
   3.500   0.8038   0.01053   0.00404  -0.0966   0.5422   0.5727
   3.750   0.8308   0.01058   0.00413  -0.0965   0.5372   0.5766
   4.000   0.8577   0.01063   0.00420  -0.0965   0.5323   0.5804
   4.250   0.8848   0.01074   0.00433  -0.0965   0.5275   0.5846
   4.500   0.9110   0.01077   0.00445  -0.0963   0.5224   0.5891
   4.750   0.9376   0.01085   0.00454  -0.0962   0.5174   0.5939
   5.000   0.9645   0.01098   0.00468  -0.0962   0.5124   0.5987
   5.250   0.9899   0.01101   0.00482  -0.0958   0.5071   0.6042
   5.500   1.0156   0.01109   0.00494  -0.0955   0.5014   0.6102
   5.750   1.0414   0.01122   0.00508  -0.0953   0.4957   0.6159
   6.000   1.0662   0.01126   0.00524  -0.0948   0.4896   0.6222
   6.500   1.1155   0.01146   0.00555  -0.0939   0.4771   0.6358
   6.750   1.1395   0.01155   0.00571  -0.0933   0.4698   0.6439
   7.000   1.1627   0.01169   0.00589  -0.0926   0.4628   0.6519
   7.250   1.1859   0.01178   0.00608  -0.0919   0.4546   0.6615
   7.500   1.2077   0.01192   0.00628  -0.0909   0.4468   0.6713
   7.750   1.2294   0.01204   0.00648  -0.0899   0.4371   0.6822
   8.000   1.2497   0.01220   0.00672  -0.0887   0.4272   0.6944
   8.250   1.2676   0.01239   0.00696  -0.0870   0.4158   0.7073
   8.500   1.2829   0.01258   0.00721  -0.0848   0.4022   0.7217
   8.750   1.2963   0.01283   0.00752  -0.0823   0.3873   0.7383
   9.000   1.3072   0.01318   0.00790  -0.0794   0.3702   0.7582
   9.250   1.3166   0.01360   0.00836  -0.0764   0.3506   0.7824
   9.500   1.3217   0.01412   0.00892  -0.0727   0.3284   0.8156
   9.750   1.3207   0.01465   0.00956  -0.0679   0.3085   0.8814
  10.000   1.3273   0.01538   0.01030  -0.0651   0.2851   1.0000
  10.250   1.3305   0.01639   0.01122  -0.0620   0.2641   1.0000
  10.500   1.3331   0.01751   0.01225  -0.0591   0.2453   1.0000
  10.750   1.3361   0.01871   0.01338  -0.0564   0.2261   1.0000
  11.000   1.3378   0.02005   0.01465  -0.0537   0.2078   1.0000
  11.250   1.3395   0.02150   0.01603  -0.0513   0.1910   1.0000
  11.500   1.3413   0.02304   0.01752  -0.0491   0.1759   1.0000
  11.750   1.3421   0.02473   0.01915  -0.0471   0.1607   1.0000
  12.000   1.3431   0.02649   0.02087  -0.0452   0.1470   1.0000
  12.250   1.3438   0.02837   0.02271  -0.0435   0.1342   1.0000
  12.500   1.3448   0.03030   0.02462  -0.0420   0.1231   1.0000
  12.750   1.3450   0.03237   0.02667  -0.0407   0.1125   1.0000
  13.000   1.3448   0.03456   0.02883  -0.0394   0.1025   1.0000
  13.250   1.3469   0.03664   0.03092  -0.0384   0.0937   1.0000
  13.500   1.3474   0.03894   0.03321  -0.0375   0.0852   1.0000
  13.750   1.3464   0.04145   0.03571  -0.0367   0.0773   1.0000
  14.000   1.3479   0.04381   0.03809  -0.0361   0.0704   1.0000
  14.250   1.3485   0.04633   0.04062  -0.0356   0.0639   1.0000
  14.500   1.3470   0.04915   0.04343  -0.0351   0.0580   1.0000
  14.750   1.3491   0.05166   0.04597  -0.0349   0.0527   1.0000
  15.000   1.3480   0.05458   0.04891  -0.0347   0.0481   1.0000
  15.250   1.3490   0.05734   0.05170  -0.0347   0.0439   1.0000
  15.500   1.3484   0.06037   0.05476  -0.0348   0.0403   1.0000
  15.750   1.3487   0.06334   0.05776  -0.0349   0.0367   1.0000
  16.000   1.3480   0.06651   0.06098  -0.0352   0.0339   1.0000
  16.250   1.3481   0.06965   0.06417  -0.0356   0.0313   1.0000
  16.500   1.3462   0.07311   0.06766  -0.0361   0.0290   1.0000
  16.750   1.3469   0.07630   0.07093  -0.0367   0.0270   1.0000
  17.000   1.3438   0.08005   0.07472  -0.0375   0.0252   1.0000
  17.250   1.3433   0.08352   0.07827  -0.0382   0.0236   1.0000
  17.500   1.3424   0.08711   0.08193  -0.0392   0.0219   1.0000
  17.750   1.3370   0.09142   0.08629  -0.0404   0.0205   1.0000
  18.000   1.3372   0.09496   0.08994  -0.0414   0.0192   1.0000
  18.250   1.3348   0.09893   0.09397  -0.0427   0.0181   1.0000
  18.500   1.3278   0.10369   0.09878  -0.0444   0.0170   1.0000
  18.750   1.3270   0.10756   0.10276  -0.0458   0.0160   1.0000
  19.000   1.3254   0.11155   0.10683  -0.0474   0.0150   1.0000
  19.250   1.3188   0.11641   0.11175  -0.0494   0.0143   1.0000
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