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EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E853 AIRFOIL (e853-il)
Reynolds number: 500,000
Max Cl/Cd: 120.78 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e853-il-500000.txt
Download as CSV file: xf-e853-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E853 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4135   0.08758   0.08547  -0.0450   1.0000   0.0160
  -9.000  -0.4209   0.08366   0.08161  -0.0456   1.0000   0.0163
  -8.750  -0.4310   0.07983   0.07783  -0.0459   1.0000   0.0165
  -7.000  -0.3601   0.02182   0.01713  -0.1007   0.9533   0.0085
  -6.750  -0.3287   0.02050   0.01561  -0.1018   0.9481   0.0081
  -6.500  -0.2955   0.01813   0.01298  -0.1036   0.9449   0.0078
  -6.250  -0.2666   0.01593   0.01052  -0.1044   0.9375   0.0078
  -6.000  -0.2301   0.01432   0.00871  -0.1066   0.9331   0.0079
  -5.750  -0.1966   0.01238   0.00653  -0.1085   0.9260   0.0085
  -5.500  -0.1593   0.01133   0.00538  -0.1110   0.9189   0.0109
  -5.250  -0.1248   0.01048   0.00440  -0.1126   0.9087   0.0168
  -5.000  -0.0913   0.00984   0.00380  -0.1142   0.8978   0.0399
  -4.750  -0.0599   0.00940   0.00340  -0.1153   0.8863   0.0667
  -4.500  -0.0308   0.00883   0.00300  -0.1160   0.8743   0.1273
  -4.250  -0.0034   0.00802   0.00257  -0.1168   0.8626   0.2508
  -4.000   0.0230   0.00743   0.00238  -0.1171   0.8510   0.3844
  -3.750   0.0508   0.00733   0.00231  -0.1171   0.8406   0.4316
  -3.500   0.0788   0.00732   0.00224  -0.1172   0.8310   0.4578
  -3.250   0.1069   0.00734   0.00219  -0.1172   0.8220   0.4792
  -3.000   0.1345   0.00737   0.00216  -0.1171   0.8129   0.4999
  -2.750   0.1626   0.00741   0.00212  -0.1172   0.8052   0.5131
  -2.500   0.1904   0.00743   0.00209  -0.1172   0.7971   0.5239
  -2.250   0.2182   0.00746   0.00207  -0.1172   0.7898   0.5347
  -2.000   0.2460   0.00750   0.00207  -0.1172   0.7827   0.5481
  -1.750   0.2738   0.00754   0.00208  -0.1172   0.7761   0.5602
  -1.500   0.3017   0.00757   0.00206  -0.1172   0.7695   0.5695
  -1.250   0.3297   0.00760   0.00205  -0.1173   0.7635   0.5768
  -1.000   0.3576   0.00761   0.00204  -0.1173   0.7572   0.5836
  -0.750   0.3859   0.00765   0.00204  -0.1175   0.7520   0.5902
  -0.500   0.4136   0.00765   0.00205  -0.1175   0.7459   0.5970
  -0.250   0.4417   0.00768   0.00207  -0.1176   0.7407   0.6037
   0.000   0.4697   0.00772   0.00210  -0.1177   0.7356   0.6109
   0.250   0.4975   0.00773   0.00214  -0.1178   0.7301   0.6182
   0.500   0.5258   0.00778   0.00217  -0.1179   0.7254   0.6259
   0.750   0.5535   0.00781   0.00224  -0.1180   0.7203   0.6341
   1.000   0.5813   0.00783   0.00230  -0.1180   0.7151   0.6423
   1.250   0.6097   0.00790   0.00236  -0.1182   0.7107   0.6518
   1.500   0.6369   0.00791   0.00244  -0.1181   0.7051   0.6613
   1.750   0.6645   0.00794   0.00252  -0.1181   0.6994   0.6714
   2.000   0.6917   0.00797   0.00261  -0.1180   0.6927   0.6827
   2.250   0.7187   0.00799   0.00267  -0.1178   0.6857   0.6949
   2.500   0.7454   0.00801   0.00277  -0.1176   0.6777   0.7083
   2.750   0.7720   0.00804   0.00284  -0.1173   0.6692   0.7231
   3.000   0.7974   0.00802   0.00291  -0.1168   0.6584   0.7394
   3.250   0.8228   0.00801   0.00299  -0.1162   0.6469   0.7579
   3.500   0.8485   0.00803   0.00310  -0.1157   0.6375   0.7791
   4.000   0.8975   0.00803   0.00335  -0.1142   0.6164   0.8336
   4.250   0.9193   0.00800   0.00347  -0.1128   0.6038   0.8725
   4.500   0.9378   0.00789   0.00352  -0.1104   0.5898   0.9509
   4.750   0.9650   0.00799   0.00361  -0.1104   0.5656   1.0000
   5.000   0.9881   0.00822   0.00377  -0.1095   0.5336   1.0000
   5.250   1.0092   0.00857   0.00398  -0.1082   0.4886   1.0000
   5.500   1.0232   0.00938   0.00438  -0.1058   0.4010   1.0000
   5.750   1.0324   0.01066   0.00508  -0.1027   0.2931   1.0000
   6.000   1.0435   0.01186   0.00579  -0.1001   0.2027   1.0000
   6.250   1.0573   0.01286   0.00644  -0.0980   0.1382   1.0000
   6.500   1.0731   0.01370   0.00705  -0.0961   0.0970   1.0000
   6.750   1.0895   0.01447   0.00764  -0.0943   0.0665   1.0000
   7.000   1.1059   0.01521   0.00828  -0.0926   0.0446   1.0000
   7.250   1.1231   0.01586   0.00886  -0.0909   0.0302   1.0000
   7.500   1.1384   0.01656   0.00952  -0.0889   0.0204   1.0000
   7.750   1.1491   0.01749   0.01044  -0.0859   0.0118   1.0000
   8.000   1.1561   0.01872   0.01176  -0.0823   0.0083   1.0000
   8.250   1.1682   0.01960   0.01272  -0.0798   0.0071   1.0000
   8.500   1.1794   0.02057   0.01377  -0.0772   0.0064   1.0000
   8.750   1.1878   0.02176   0.01505  -0.0743   0.0059   1.0000
   9.000   1.1933   0.02323   0.01663  -0.0712   0.0056   1.0000
   9.250   1.1969   0.02506   0.01861  -0.0679   0.0054   1.0000
   9.500   1.2043   0.02683   0.02051  -0.0654   0.0054   1.0000
   9.750   1.2136   0.02878   0.02261  -0.0632   0.0053   1.0000
  10.000   1.2252   0.03082   0.02484  -0.0613   0.0053   1.0000
  10.250   1.2379   0.03304   0.02725  -0.0597   0.0053   1.0000
  10.500   1.2498   0.03498   0.02936  -0.0581   0.0054   1.0000
  10.750   1.2598   0.03712   0.03169  -0.0563   0.0054   1.0000
  11.000   1.2676   0.03927   0.03404  -0.0545   0.0055   1.0000
  11.250   1.2725   0.04177   0.03679  -0.0525   0.0057   1.0000
  11.500   1.2533   0.05041   0.04629  -0.0483   0.0070   1.0000
  11.750   1.2337   0.05578   0.05202  -0.0457   0.0074   1.0000
  12.000   1.2152   0.06060   0.05710  -0.0440   0.0076   1.0000
  12.250   1.1935   0.06595   0.06269  -0.0432   0.0079   1.0000
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