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EPPLER 593 AIRFOIL (e593-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 593 AIRFOIL (e593-il)
Reynolds number: 1,000,000
Max Cl/Cd: 148.09 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e593-il-1000000.txt
Download as CSV file: xf-e593-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 593 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3171   0.08909   0.08603   0.0046   0.4743   0.0129
  -8.500  -0.3162   0.08437   0.08132   0.0027   0.4734   0.0129
  -8.250  -0.3158   0.07968   0.07665   0.0008   0.4724   0.0129
  -8.000  -0.3200   0.07459   0.07157  -0.0009   0.4716   0.0132
  -7.750  -0.3182   0.07103   0.06801  -0.0022   0.4703   0.0133
  -7.500  -0.4977   0.03050   0.02647  -0.0375   0.4785   0.0079
  -7.250  -0.4828   0.02638   0.02202  -0.0379   0.4771   0.0075
  -7.000  -0.4668   0.02193   0.01701  -0.0380   0.4756   0.0072
  -6.750  -0.4453   0.01934   0.01400  -0.0376   0.4740   0.0069
  -6.500  -0.4215   0.01752   0.01185  -0.0371   0.4723   0.0068
  -6.250  -0.3963   0.01619   0.01027  -0.0367   0.4704   0.0067
  -6.000  -0.3703   0.01518   0.00905  -0.0363   0.4683   0.0066
  -5.750  -0.3438   0.01438   0.00808  -0.0359   0.4656   0.0066
  -5.500  -0.3168   0.01364   0.00722  -0.0356   0.4644   0.0067
  -5.250  -0.2896   0.01303   0.00650  -0.0352   0.4631   0.0067
  -5.000  -0.2621   0.01249   0.00587  -0.0350   0.4616   0.0068
  -4.750  -0.2344   0.01201   0.00531  -0.0347   0.4601   0.0070
  -4.500  -0.2065   0.01159   0.00481  -0.0344   0.4585   0.0071
  -4.250  -0.1785   0.01122   0.00436  -0.0342   0.4569   0.0074
  -4.000  -0.1504   0.01091   0.00399  -0.0340   0.4553   0.0077
  -3.750  -0.1225   0.01049   0.00350  -0.0337   0.4536   0.0088
  -3.500  -0.0945   0.01022   0.00316  -0.0334   0.4515   0.0110
  -3.250  -0.0667   0.00988   0.00287  -0.0332   0.4494   0.0237
  -3.000  -0.0384   0.00967   0.00270  -0.0331   0.4485   0.0326
  -2.750  -0.0100   0.00951   0.00257  -0.0330   0.4473   0.0399
  -2.500   0.0185   0.00937   0.00246  -0.0329   0.4460   0.0475
  -2.250   0.0469   0.00925   0.00236  -0.0328   0.4447   0.0559
  -2.000   0.0754   0.00914   0.00228  -0.0327   0.4432   0.0669
  -1.750   0.1039   0.00904   0.00221  -0.0326   0.4418   0.0776
  -1.500   0.1324   0.00895   0.00214  -0.0325   0.4403   0.0882
  -1.250   0.1610   0.00889   0.00207  -0.0324   0.4387   0.0973
  -1.000   0.1895   0.00884   0.00202  -0.0324   0.4370   0.1081
  -0.750   0.2178   0.00882   0.00202  -0.0323   0.4350   0.1207
  -0.500   0.2463   0.00878   0.00200  -0.0322   0.4337   0.1341
  -0.250   0.2749   0.00869   0.00197  -0.0322   0.4328   0.1501
   0.000   0.3035   0.00861   0.00194  -0.0322   0.4317   0.1706
   0.250   0.3320   0.00851   0.00193  -0.0321   0.4304   0.2017
   0.500   0.3603   0.00838   0.00193  -0.0321   0.4290   0.2475
   0.750   0.3884   0.00820   0.00193  -0.0321   0.4275   0.3133
   1.000   0.4146   0.00763   0.00195  -0.0319   0.4260   0.5303
   1.250   0.4435   0.00649   0.00202  -0.0318   0.4247   0.9726
   1.500   0.4949   0.00653   0.00200  -0.0368   0.4231   1.0000
   1.750   0.5221   0.00662   0.00204  -0.0364   0.4215   1.0000
   2.000   0.5491   0.00677   0.00213  -0.0361   0.4194   1.0000
   2.250   0.5765   0.00682   0.00217  -0.0359   0.4183   1.0000
   2.500   0.6039   0.00687   0.00220  -0.0356   0.4171   1.0000
   2.750   0.6314   0.00692   0.00225  -0.0354   0.4159   1.0000
   3.000   0.6590   0.00697   0.00229  -0.0352   0.4143   1.0000
   3.250   0.6865   0.00702   0.00233  -0.0350   0.4127   1.0000
   3.500   0.7142   0.00708   0.00237  -0.0348   0.4110   1.0000
   3.750   0.7418   0.00713   0.00241  -0.0347   0.4093   1.0000
   4.000   0.7695   0.00720   0.00246  -0.0345   0.4071   1.0000
   4.250   0.7968   0.00737   0.00259  -0.0343   0.4042   1.0000
   4.500   0.8248   0.00739   0.00263  -0.0343   0.4027   1.0000
   4.750   0.8527   0.00742   0.00268  -0.0342   0.4008   1.0000
   5.000   0.8806   0.00746   0.00274  -0.0341   0.3985   1.0000
   5.250   0.9085   0.00750   0.00279  -0.0341   0.3962   1.0000
   5.500   0.9364   0.00756   0.00284  -0.0340   0.3937   1.0000
   5.750   0.9639   0.00768   0.00294  -0.0339   0.3905   1.0000
   6.000   0.9919   0.00773   0.00303  -0.0339   0.3881   1.0000
   6.250   1.0199   0.00777   0.00311  -0.0339   0.3855   1.0000
   6.500   1.0478   0.00782   0.00320  -0.0339   0.3825   1.0000
   6.750   1.0756   0.00789   0.00327  -0.0339   0.3794   1.0000
   7.000   1.1030   0.00803   0.00339  -0.0339   0.3755   1.0000
   7.250   1.1311   0.00805   0.00349  -0.0339   0.3719   1.0000
   7.500   1.1590   0.00811   0.00358  -0.0340   0.3672   1.0000
   7.750   1.1864   0.00823   0.00370  -0.0340   0.3623   1.0000
   8.000   1.2141   0.00832   0.00384  -0.0340   0.3574   1.0000
   8.250   1.2416   0.00843   0.00397  -0.0340   0.3509   1.0000
   8.500   1.2689   0.00857   0.00413  -0.0340   0.3441   1.0000
   8.750   1.2958   0.00875   0.00431  -0.0340   0.3341   1.0000
   9.000   1.3225   0.00896   0.00452  -0.0340   0.3219   1.0000
   9.250   1.3484   0.00928   0.00481  -0.0340   0.3056   1.0000
   9.500   1.3733   0.00973   0.00519  -0.0339   0.2824   1.0000
   9.750   1.3963   0.01044   0.00577  -0.0337   0.2530   1.0000
  10.000   1.4184   0.01123   0.00643  -0.0334   0.2256   1.0000
  10.250   1.4402   0.01202   0.00712  -0.0331   0.2015   1.0000
  10.500   1.4608   0.01290   0.00788  -0.0327   0.1779   1.0000
  10.750   1.4804   0.01382   0.00870  -0.0322   0.1550   1.0000
  11.000   1.4999   0.01469   0.00950  -0.0317   0.1371   1.0000
  11.250   1.5185   0.01557   0.01033  -0.0312   0.1214   1.0000
  11.500   1.5358   0.01651   0.01122  -0.0306   0.1076   1.0000
  11.750   1.5508   0.01757   0.01223  -0.0298   0.0944   1.0000
  12.000   1.5640   0.01867   0.01331  -0.0288   0.0839   1.0000
  12.250   1.5716   0.02008   0.01469  -0.0276   0.0730   1.0000
  12.500   1.5716   0.02170   0.01634  -0.0257   0.0673   1.0000
  12.750   1.5595   0.02516   0.01993  -0.0259   0.0644   1.0000
  13.000   1.5544   0.02869   0.02354  -0.0268   0.0617   1.0000
  13.250   1.5394   0.03294   0.02781  -0.0272   0.0566   1.0000
  13.500   1.5298   0.03647   0.03139  -0.0273   0.0528   1.0000
  13.750   1.5166   0.04032   0.03527  -0.0274   0.0493   1.0000
  14.000   1.5076   0.04375   0.03874  -0.0275   0.0457   1.0000
  14.250   1.4997   0.04709   0.04212  -0.0276   0.0431   1.0000
  14.500   1.4897   0.05068   0.04572  -0.0279   0.0398   1.0000
  14.750   1.4831   0.05404   0.04912  -0.0282   0.0363   1.0000
  15.000   1.4811   0.05704   0.05217  -0.0286   0.0349   1.0000
  15.250   1.4766   0.06048   0.05565  -0.0292   0.0322   1.0000
  15.500   1.4749   0.06361   0.05880  -0.0298   0.0295   1.0000
  15.750   1.4699   0.06725   0.06248  -0.0305   0.0270   1.0000
  16.000   1.4708   0.07018   0.06546  -0.0311   0.0255   1.0000
  16.250   1.4652   0.07403   0.06932  -0.0321   0.0226   1.0000
  16.500   1.4657   0.07715   0.07249  -0.0328   0.0214   1.0000
  16.750   1.4633   0.08071   0.07610  -0.0338   0.0196   1.0000
  17.000   1.4605   0.08435   0.07977  -0.0349   0.0180   1.0000
  17.250   1.4594   0.08787   0.08336  -0.0359   0.0169   1.0000
  17.500   1.4576   0.09154   0.08706  -0.0371   0.0155   1.0000
  17.750   1.4533   0.09562   0.09119  -0.0385   0.0143   1.0000
  18.000   1.4533   0.09910   0.09475  -0.0397   0.0136   1.0000
  18.250   1.4506   0.10307   0.09878  -0.0412   0.0127   1.0000
  18.500   1.4475   0.10717   0.10293  -0.0428   0.0118   1.0000
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