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EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E852 AIRFOIL (e852-il)
Reynolds number: 1,000,000
Max Cl/Cd: 106.55 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e852-il-1000000-n5.txt
Download as CSV file: xf-e852-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E852 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4569   0.08068   0.07912  -0.0513   0.9970   0.0013
  -9.500  -0.4627   0.07150   0.06996  -0.0595   0.9948   0.0013
  -9.000  -0.4950   0.04420   0.04239  -0.0917   0.9798   0.0011
  -8.500  -0.5152   0.02209   0.01883  -0.0984   0.9501   0.0015
  -8.250  -0.4828   0.02042   0.01692  -0.1010   0.9457   0.0016
  -8.000  -0.4491   0.01882   0.01510  -0.1036   0.9405   0.0017
  -7.750  -0.4150   0.01749   0.01355  -0.1061   0.9330   0.0017
  -7.500  -0.3841   0.01582   0.01159  -0.1079   0.9224   0.0018
  -7.250  -0.3595   0.01362   0.00900  -0.1083   0.9084   0.0020
  -7.000  -0.3344   0.01259   0.00777  -0.1083   0.8959   0.0021
  -6.750  -0.3095   0.01187   0.00688  -0.1082   0.8847   0.0022
  -6.500  -0.2849   0.01118   0.00604  -0.1079   0.8742   0.0023
  -6.000  -0.2337   0.01041   0.00506  -0.1076   0.8561   0.0027
  -5.750  -0.2076   0.01011   0.00469  -0.1075   0.8486   0.0031
  -5.500  -0.1819   0.00966   0.00412  -0.1073   0.8409   0.0033
  -5.250  -0.1558   0.00920   0.00354  -0.1071   0.8341   0.0034
  -5.000  -0.1293   0.00883   0.00304  -0.1070   0.8276   0.0036
  -4.750  -0.1024   0.00854   0.00264  -0.1069   0.8220   0.0038
  -4.500  -0.0752   0.00827   0.00228  -0.1068   0.8160   0.0057
  -4.250  -0.0483   0.00801   0.00203  -0.1068   0.8107   0.0161
  -4.000  -0.0209   0.00779   0.00182  -0.1069   0.8054   0.0290
  -3.750   0.0062   0.00756   0.00165  -0.1070   0.8003   0.0530
  -3.500   0.0334   0.00728   0.00148  -0.1072   0.7957   0.0919
  -3.250   0.0606   0.00696   0.00132  -0.1073   0.7910   0.1450
  -3.000   0.0876   0.00662   0.00116  -0.1075   0.7865   0.2124
  -2.750   0.1145   0.00618   0.00101  -0.1078   0.7825   0.3104
  -2.500   0.1421   0.00595   0.00092  -0.1080   0.7781   0.3669
  -2.250   0.1697   0.00579   0.00088  -0.1081   0.7739   0.4184
  -2.000   0.1976   0.00574   0.00085  -0.1083   0.7702   0.4395
  -1.750   0.2257   0.00570   0.00083  -0.1084   0.7663   0.4577
  -1.500   0.2537   0.00564   0.00081  -0.1086   0.7623   0.4818
  -1.250   0.2816   0.00562   0.00080  -0.1087   0.7587   0.5004
  -1.000   0.3098   0.00560   0.00080  -0.1088   0.7551   0.5133
  -0.750   0.3380   0.00559   0.00081  -0.1090   0.7512   0.5232
  -0.500   0.3660   0.00559   0.00081  -0.1091   0.7473   0.5302
  -0.250   0.3939   0.00561   0.00083  -0.1092   0.7433   0.5371
   0.000   0.4220   0.00560   0.00084  -0.1093   0.7381   0.5436
   0.250   0.4496   0.00563   0.00086  -0.1093   0.7320   0.5504
   0.500   0.4773   0.00563   0.00088  -0.1093   0.7247   0.5572
   0.750   0.5045   0.00567   0.00091  -0.1092   0.7162   0.5643
   1.000   0.5317   0.00570   0.00095  -0.1092   0.7060   0.5714
   1.500   0.5856   0.00578   0.00103  -0.1089   0.6806   0.5870
   1.750   0.6117   0.00586   0.00108  -0.1085   0.6605   0.5952
   2.000   0.6365   0.00600   0.00116  -0.1080   0.6287   0.6041
   2.250   0.6606   0.00620   0.00126  -0.1073   0.5905   0.6130
   2.500   0.6832   0.00653   0.00142  -0.1063   0.5364   0.6223
   3.000   0.7206   0.00787   0.00202  -0.1031   0.3508   0.6430
   3.250   0.7403   0.00849   0.00234  -0.1018   0.2696   0.6543
   3.500   0.7558   0.00947   0.00279  -0.0998   0.1470   0.6662
   3.750   0.7737   0.01027   0.00323  -0.0982   0.0600   0.6790
   4.000   0.7972   0.01060   0.00350  -0.0975   0.0372   0.6937
   4.250   0.8206   0.01093   0.00378  -0.0968   0.0200   0.7097
   4.750   0.8670   0.01160   0.00447  -0.0953   0.0015   0.7460
   5.000   0.8911   0.01184   0.00480  -0.0946   0.0012   0.7682
   5.250   0.9147   0.01209   0.00517  -0.0939   0.0012   0.7932
   5.500   0.9374   0.01237   0.00560  -0.0929   0.0011   0.8232
   5.750   0.9585   0.01264   0.00609  -0.0916   0.0010   0.8654
   6.000   0.9765   0.01281   0.00651  -0.0895   0.0010   1.0000
   6.250   0.9983   0.01333   0.00710  -0.0884   0.0010   1.0000
   6.500   1.0191   0.01395   0.00781  -0.0872   0.0010   1.0000
   6.750   1.0394   0.01461   0.00855  -0.0858   0.0010   1.0000
   7.000   1.0587   0.01537   0.00941  -0.0843   0.0010   1.0000
   7.250   1.0768   0.01628   0.01043  -0.0826   0.0010   1.0000
   7.500   1.0945   0.01727   0.01154  -0.0809   0.0010   1.0000
   7.750   1.1117   0.01843   0.01283  -0.0791   0.0010   1.0000
   8.000   1.1286   0.01984   0.01440  -0.0772   0.0010   1.0000
   8.250   1.1462   0.02138   0.01613  -0.0756   0.0010   1.0000
   8.500   1.1632   0.02333   0.01830  -0.0738   0.0011   1.0000
   8.750   1.1792   0.02544   0.02065  -0.0720   0.0011   1.0000
   9.000   1.1918   0.02810   0.02366  -0.0697   0.0011   1.0000
   9.250   1.1997   0.03119   0.02709  -0.0668   0.0012   1.0000
   9.500   1.2024   0.03437   0.03060  -0.0633   0.0012   1.0000
   9.750   1.1966   0.03766   0.03420  -0.0586   0.0012   1.0000
  10.000   1.1862   0.04089   0.03771  -0.0536   0.0012   1.0000
  10.250   1.1709   0.04444   0.04153  -0.0486   0.0013   1.0000
  10.500   1.1539   0.04811   0.04545  -0.0444   0.0013   1.0000
  10.750   1.1361   0.05198   0.04952  -0.0411   0.0013   1.0000
  11.000   1.1133   0.05671   0.05447  -0.0385   0.0013   1.0000
  11.250   1.0910   0.06176   0.05971  -0.0372   0.0013   1.0000
  11.500   1.0679   0.06741   0.06553  -0.0371   0.0014   1.0000
  11.750   1.0444   0.07379   0.07207  -0.0385   0.0014   1.0000
  12.000   1.0260   0.08010   0.07850  -0.0410   0.0013   1.0000
  12.250   1.0003   0.08917   0.08771  -0.0460   0.0014   1.0000
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