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EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E852 AIRFOIL (e852-il)
Reynolds number: 1,000,000
Max Cl/Cd: 132.11 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e852-il-1000000.txt
Download as CSV file: xf-e852-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.2982   0.01640   0.01225  -0.1048   0.9466   0.0045
  -6.250  -0.2667   0.01369   0.00920  -0.1064   0.9411   0.0047
  -6.000  -0.2356   0.01201   0.00731  -0.1077   0.9333   0.0049
  -5.750  -0.2053   0.01088   0.00604  -0.1087   0.9241   0.0054
  -5.500  -0.1754   0.01028   0.00534  -0.1094   0.9143   0.0060
  -5.000  -0.1215   0.00895   0.00369  -0.1094   0.8936   0.0065
  -4.750  -0.0947   0.00845   0.00303  -0.1093   0.8845   0.0068
  -4.250  -0.0410   0.00757   0.00206  -0.1090   0.8680   0.0418
  -4.000  -0.0140   0.00728   0.00183  -0.1091   0.8610   0.0760
  -3.750   0.0124   0.00684   0.00161  -0.1092   0.8540   0.1473
  -3.500   0.0379   0.00609   0.00135  -0.1095   0.8477   0.2967
  -3.250   0.0645   0.00568   0.00124  -0.1096   0.8415   0.4014
  -3.000   0.0922   0.00558   0.00119  -0.1097   0.8362   0.4418
  -2.750   0.1200   0.00552   0.00115  -0.1098   0.8306   0.4685
  -2.500   0.1480   0.00550   0.00109  -0.1099   0.8256   0.4850
  -2.250   0.1759   0.00547   0.00108  -0.1100   0.8208   0.5031
  -2.000   0.2039   0.00546   0.00105  -0.1101   0.8159   0.5144
  -1.750   0.2321   0.00547   0.00103  -0.1102   0.8114   0.5260
  -1.500   0.2601   0.00545   0.00102  -0.1103   0.8070   0.5412
  -1.250   0.2881   0.00544   0.00102  -0.1104   0.8025   0.5544
  -0.750   0.3443   0.00545   0.00103  -0.1107   0.7943   0.5746
  -0.500   0.3723   0.00544   0.00104  -0.1108   0.7899   0.5825
  -0.250   0.4004   0.00547   0.00105  -0.1109   0.7855   0.5908
   0.000   0.4282   0.00546   0.00107  -0.1110   0.7805   0.5989
   0.250   0.4559   0.00546   0.00109  -0.1110   0.7749   0.6075
   0.500   0.4836   0.00548   0.00111  -0.1110   0.7689   0.6168
   0.750   0.5110   0.00547   0.00114  -0.1110   0.7618   0.6261
   1.000   0.5383   0.00549   0.00117  -0.1109   0.7547   0.6362
   1.250   0.5656   0.00549   0.00120  -0.1108   0.7469   0.6472
   1.750   0.6194   0.00551   0.00128  -0.1105   0.7274   0.6717
   2.000   0.6459   0.00553   0.00135  -0.1102   0.7155   0.6853
   2.250   0.6726   0.00555   0.00141  -0.1100   0.7049   0.6999
   2.500   0.6994   0.00556   0.00149  -0.1098   0.6937   0.7158
   2.750   0.7252   0.00561   0.00156  -0.1094   0.6771   0.7334
   3.000   0.7504   0.00568   0.00165  -0.1088   0.6533   0.7528
   3.250   0.7709   0.00596   0.00177  -0.1073   0.5900   0.7741
   3.500   0.7722   0.00767   0.00243  -0.1024   0.3448   0.7986
   3.750   0.7871   0.00855   0.00287  -0.1002   0.2288   0.8280
   4.000   0.8031   0.00921   0.00326  -0.0981   0.1445   0.8667
   4.250   0.8166   0.00954   0.00355  -0.0951   0.0956   0.9419
   4.500   0.8395   0.01019   0.00392  -0.0945   0.0407   1.0000
   4.750   0.8594   0.01090   0.00440  -0.0932   0.0051   1.0000
   5.000   0.8832   0.01128   0.00481  -0.0924   0.0029   1.0000
   5.250   0.9069   0.01166   0.00525  -0.0916   0.0026   1.0000
   5.500   0.9297   0.01213   0.00580  -0.0907   0.0024   1.0000
   5.750   0.9518   0.01265   0.00644  -0.0896   0.0024   1.0000
   6.000   0.9731   0.01325   0.00713  -0.0884   0.0024   1.0000
   6.250   0.9927   0.01403   0.00802  -0.0868   0.0024   1.0000
   6.500   1.0099   0.01508   0.00922  -0.0846   0.0025   1.0000
   6.750   1.0256   0.01645   0.01075  -0.0823   0.0027   1.0000
   7.000   1.0420   0.01851   0.01303  -0.0799   0.0030   1.0000
   7.250   1.0634   0.02255   0.01741  -0.0783   0.0038   1.0000
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