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EPPLER 678 AIRFOIL (e678-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 678 AIRFOIL (e678-il)
Reynolds number: 500,000
Max Cl/Cd: 116.76 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e678-il-500000.txt
Download as CSV file: xf-e678-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 678 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000   0.0458   0.10761   0.10504  -0.1371   0.9519   0.0205
 -12.750   0.0558   0.10455   0.10198  -0.1391   0.9515   0.0214
 -12.500  -0.0577   0.11392   0.11124  -0.1332   0.9570   0.0199
 -12.250  -0.0484   0.11146   0.10878  -0.1340   0.9554   0.0202
 -12.000  -0.0371   0.10898   0.10630  -0.1353   0.9542   0.0207
 -11.750  -0.0277   0.10585   0.10317  -0.1373   0.9532   0.0212
 -11.500  -0.0182   0.10226   0.09958  -0.1401   0.9524   0.0225
 -11.000   0.0794   0.07911   0.07656  -0.1495   0.9434   0.0255
 -10.750   0.0855   0.07591   0.07337  -0.1507   0.9419   0.0260
 -10.500   0.0916   0.07202   0.06948  -0.1529   0.9409   0.0268
 -10.250   0.0949   0.06744   0.06489  -0.1555   0.9398   0.0279
 -10.000   0.0793   0.05819   0.05567  -0.1623   0.9386   0.0296
  -9.750   0.0183   0.07562   0.07299  -0.1571   0.9410   0.0265
  -9.500   0.0263   0.07100   0.06838  -0.1616   0.9396   0.0273
  -9.250   0.0302   0.06393   0.06131  -0.1694   0.9381   0.0285
  -7.750  -0.1252   0.02917   0.02471  -0.1680   0.8993   0.0196
  -7.500  -0.1012   0.02452   0.01981  -0.1701   0.8975   0.0180
  -7.250  -0.0702   0.02094   0.01570  -0.1723   0.8961   0.0172
  -7.000  -0.0337   0.01900   0.01348  -0.1748   0.8949   0.0173
  -6.750   0.0050   0.01756   0.01184  -0.1776   0.8938   0.0177
  -6.500   0.0144   0.01692   0.01111  -0.1741   0.8879   0.0179
  -6.250   0.0407   0.01611   0.01021  -0.1741   0.8842   0.0185
  -6.000   0.0766   0.01531   0.00929  -0.1760   0.8819   0.0193
  -5.750   0.1141   0.01423   0.00812  -0.1785   0.8798   0.0198
  -5.500   0.1424   0.01331   0.00717  -0.1791   0.8761   0.0206
  -5.250   0.1592   0.01283   0.00669  -0.1771   0.8693   0.0215
  -5.000   0.1951   0.01221   0.00600  -0.1791   0.8656   0.0232
  -4.750   0.2237   0.01163   0.00537  -0.1796   0.8604   0.0251
  -4.500   0.2452   0.01122   0.00494  -0.1785   0.8524   0.0281
  -4.250   0.2806   0.01065   0.00437  -0.1804   0.8474   0.0398
  -4.000   0.2965   0.01014   0.00402  -0.1782   0.8362   0.0752
  -3.750   0.3160   0.00975   0.00376  -0.1768   0.8238   0.1139
  -3.500   0.3369   0.00935   0.00350  -0.1757   0.8087   0.1640
  -3.250   0.3663   0.00882   0.00320  -0.1767   0.7922   0.2521
  -3.000   0.4019   0.00817   0.00293  -0.1792   0.7764   0.3994
  -2.750   0.4359   0.00780   0.00280  -0.1811   0.7630   0.5184
  -2.500   0.4666   0.00771   0.00278  -0.1819   0.7530   0.5854
  -2.250   0.4966   0.00777   0.00283  -0.1825   0.7457   0.6298
  -2.000   0.5259   0.00789   0.00292  -0.1829   0.7398   0.6616
  -1.750   0.5568   0.00807   0.00301  -0.1836   0.7350   0.6875
  -1.500   0.5856   0.00822   0.00312  -0.1839   0.7309   0.7040
  -1.250   0.6135   0.00837   0.00324  -0.1840   0.7269   0.7159
  -1.000   0.6431   0.00854   0.00335  -0.1845   0.7230   0.7272
  -0.750   0.6751   0.00874   0.00346  -0.1855   0.7195   0.7376
  -0.500   0.7037   0.00890   0.00361  -0.1858   0.7166   0.7459
  -0.250   0.7312   0.00905   0.00373  -0.1859   0.7137   0.7556
   0.000   0.7577   0.00918   0.00388  -0.1856   0.7107   0.7621
   0.250   0.7868   0.00933   0.00399  -0.1861   0.7078   0.7694
   0.500   0.8168   0.00948   0.00410  -0.1867   0.7050   0.7745
   0.750   0.8492   0.00968   0.00426  -0.1879   0.7023   0.7797
   1.000   0.8757   0.00979   0.00438  -0.1879   0.6998   0.7857
   1.250   0.9007   0.00988   0.00450  -0.1874   0.6967   0.7903
   1.500   0.9267   0.01000   0.00463  -0.1872   0.6930   0.7950
   1.750   0.9555   0.01014   0.00474  -0.1876   0.6891   0.8000
   2.000   0.9877   0.01034   0.00489  -0.1888   0.6855   0.8039
   2.250   1.0094   0.01039   0.00501  -0.1877   0.6822   0.8075
   2.500   1.0341   0.01048   0.00512  -0.1872   0.6786   0.8115
   2.750   1.0615   0.01059   0.00523  -0.1874   0.6749   0.8156
   3.000   1.0913   0.01073   0.00534  -0.1881   0.6714   0.8191
   3.250   1.1165   0.01084   0.00549  -0.1878   0.6677   0.8221
   3.500   1.1382   0.01090   0.00562  -0.1867   0.6638   0.8258
   3.750   1.1631   0.01098   0.00572  -0.1863   0.6598   0.8296
   4.000   1.1911   0.01109   0.00582  -0.1867   0.6560   0.8333
   4.250   1.2163   0.01120   0.00596  -0.1864   0.6520   0.8364
   4.500   1.2344   0.01123   0.00609  -0.1845   0.6472   0.8401
   4.750   1.2564   0.01128   0.00617  -0.1835   0.6423   0.8443
   5.000   1.2848   0.01141   0.00628  -0.1839   0.6378   0.8481
   5.250   1.2984   0.01142   0.00640  -0.1811   0.6328   0.8518
   5.500   1.3143   0.01145   0.00649  -0.1788   0.6275   0.8558
   5.750   1.3378   0.01155   0.00658  -0.1781   0.6223   0.8595
   6.000   1.3508   0.01165   0.00678  -0.1753   0.6161   0.8639
   6.250   1.3658   0.01172   0.00691  -0.1728   0.6096   0.8676
   6.500   1.3824   0.01184   0.00709  -0.1708   0.6029   0.8717
   6.750   1.3964   0.01198   0.00729  -0.1682   0.5946   0.8765
   7.000   1.4098   0.01214   0.00751  -0.1656   0.5849   0.8811
   7.250   1.4209   0.01235   0.00776  -0.1625   0.5730   0.8860
   7.500   1.4304   0.01264   0.00808  -0.1592   0.5566   0.8917
   7.750   1.4352   0.01306   0.00847  -0.1550   0.5325   0.8979
   8.000   1.4375   0.01371   0.00902  -0.1506   0.5010   0.9057
   8.250   1.4372   0.01455   0.00973  -0.1458   0.4658   0.9142
   8.500   1.4355   0.01558   0.01061  -0.1410   0.4301   0.9253
   8.750   1.4336   0.01663   0.01154  -0.1363   0.3967   0.9460
   9.000   1.4349   0.01784   0.01260  -0.1325   0.3622   1.0000
   9.250   1.4403   0.01914   0.01375  -0.1297   0.3317   1.0000
   9.500   1.4468   0.02041   0.01491  -0.1272   0.3036   1.0000
   9.750   1.4519   0.02180   0.01616  -0.1245   0.2755   1.0000
  10.000   1.4558   0.02329   0.01753  -0.1217   0.2483   1.0000
  10.250   1.4586   0.02490   0.01900  -0.1189   0.2202   1.0000
  10.500   1.4617   0.02656   0.02053  -0.1163   0.1958   1.0000
  10.750   1.4654   0.02824   0.02210  -0.1138   0.1718   1.0000
  11.000   1.4689   0.02999   0.02375  -0.1115   0.1500   1.0000
  11.250   1.4717   0.03186   0.02552  -0.1092   0.1287   1.0000
  11.500   1.4747   0.03379   0.02737  -0.1071   0.1091   1.0000
  11.750   1.4771   0.03586   0.02934  -0.1051   0.0898   1.0000
  12.000   1.4777   0.03815   0.03153  -0.1031   0.0698   1.0000
  12.250   1.4758   0.04079   0.03403  -0.1010   0.0486   1.0000
  12.500   1.4705   0.04388   0.03697  -0.0989   0.0294   1.0000
  12.750   1.4716   0.04645   0.03952  -0.0974   0.0214   1.0000
  13.000   1.4747   0.04888   0.04198  -0.0961   0.0185   1.0000
  13.250   1.4815   0.05098   0.04416  -0.0952   0.0171   1.0000
  13.500   1.4866   0.05328   0.04654  -0.0943   0.0160   1.0000
  13.750   1.4885   0.05598   0.04930  -0.0933   0.0149   1.0000
  14.000   1.4923   0.05851   0.05192  -0.0925   0.0143   1.0000
  14.250   1.4968   0.06099   0.05450  -0.0918   0.0138   1.0000
  14.500   1.5004   0.06364   0.05724  -0.0911   0.0133   1.0000
  14.750   1.5025   0.06649   0.06018  -0.0906   0.0130   1.0000
  15.000   1.5040   0.06948   0.06327  -0.0901   0.0126   1.0000
  15.250   1.5041   0.07269   0.06656  -0.0897   0.0123   1.0000
  15.500   1.5020   0.07624   0.07022  -0.0893   0.0120   1.0000
  15.750   1.4972   0.08025   0.07433  -0.0891   0.0118   1.0000
  16.000   1.4902   0.08463   0.07882  -0.0890   0.0115   1.0000
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