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EPPLER 678 AIRFOIL (e678-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 678 AIRFOIL (e678-il)
Reynolds number: 500,000
Max Cl/Cd: 109.59 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e678-il-500000-n5.txt
Download as CSV file: xf-e678-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.0048   0.08318   0.08026  -0.1614   0.9314   0.0082
 -11.500  -0.1397   0.04598   0.04272  -0.1849   0.9236   0.0080
 -11.250  -0.1617   0.03898   0.03548  -0.1911   0.9176   0.0080
 -11.000  -0.1772   0.03451   0.03077  -0.1940   0.9120   0.0080
 -10.750  -0.1865   0.03107   0.02706  -0.1956   0.9076   0.0080
 -10.500  -0.1995   0.02919   0.02506  -0.1930   0.9027   0.0079
 -10.250  -0.2104   0.02743   0.02310  -0.1902   0.8977   0.0080
 -10.000  -0.2094   0.02571   0.02113  -0.1890   0.8943   0.0080
  -9.750  -0.2045   0.02428   0.01947  -0.1874   0.8913   0.0081
  -9.500  -0.1996   0.02306   0.01808  -0.1850   0.8878   0.0081
  -9.250  -0.1895   0.02179   0.01661  -0.1834   0.8845   0.0082
  -9.000  -0.1752   0.02032   0.01495  -0.1826   0.8815   0.0083
  -8.750  -0.1535   0.01925   0.01373  -0.1828   0.8790   0.0085
  -8.500  -0.1353   0.01848   0.01286  -0.1819   0.8758   0.0087
  -8.250  -0.1192   0.01793   0.01225  -0.1804   0.8722   0.0089
  -8.000  -0.0993   0.01733   0.01156  -0.1796   0.8688   0.0093
  -7.750  -0.0759   0.01659   0.01071  -0.1795   0.8658   0.0095
  -7.500  -0.0491   0.01583   0.00980  -0.1800   0.8632   0.0099
  -7.250  -0.0316   0.01526   0.00917  -0.1784   0.8592   0.0100
  -7.000  -0.0133   0.01470   0.00854  -0.1770   0.8543   0.0102
  -6.750   0.0116   0.01411   0.00786  -0.1770   0.8499   0.0105
  -6.500   0.0334   0.01363   0.00730  -0.1762   0.8443   0.0107
  -6.250   0.0518   0.01313   0.00675  -0.1747   0.8366   0.0110
  -6.000   0.0727   0.01262   0.00620  -0.1738   0.8284   0.0113
  -5.750   0.0920   0.01223   0.00576  -0.1723   0.8153   0.0118
  -5.500   0.1168   0.01182   0.00522  -0.1720   0.7828   0.0122
  -5.250   0.1398   0.01160   0.00469  -0.1711   0.7452   0.0128
  -5.000   0.1595   0.01149   0.00440  -0.1697   0.7306   0.0136
  -4.750   0.1828   0.01130   0.00412  -0.1691   0.7221   0.0147
  -4.500   0.2078   0.01116   0.00388  -0.1689   0.7158   0.0162
  -4.250   0.2341   0.01099   0.00366  -0.1688   0.7108   0.0182
  -4.000   0.2608   0.01082   0.00346  -0.1689   0.7061   0.0229
  -3.750   0.2886   0.01065   0.00330  -0.1693   0.7018   0.0386
  -3.500   0.3167   0.01048   0.00317  -0.1698   0.6984   0.0570
  -3.250   0.3447   0.01027   0.00305  -0.1703   0.6954   0.0855
  -3.000   0.3734   0.01003   0.00296  -0.1710   0.6924   0.1310
  -2.750   0.4030   0.00978   0.00288  -0.1719   0.6896   0.1896
  -2.500   0.4341   0.00946   0.00281  -0.1733   0.6870   0.2794
  -2.250   0.4660   0.00920   0.00278  -0.1748   0.6846   0.3679
  -2.000   0.4970   0.00903   0.00277  -0.1760   0.6824   0.4353
  -1.750   0.5269   0.00882   0.00279  -0.1769   0.6800   0.5167
  -1.500   0.5559   0.00870   0.00284  -0.1774   0.6775   0.5768
  -1.250   0.5841   0.00870   0.00292  -0.1777   0.6751   0.6157
  -1.000   0.6122   0.00874   0.00301  -0.1780   0.6729   0.6467
  -0.750   0.6405   0.00882   0.00309  -0.1782   0.6709   0.6683
  -0.500   0.6694   0.00892   0.00316  -0.1786   0.6689   0.6844
   0.000   0.7253   0.00911   0.00333  -0.1790   0.6649   0.7093
   0.250   0.7519   0.00918   0.00340  -0.1789   0.6627   0.7181
   0.500   0.7788   0.00925   0.00348  -0.1789   0.6607   0.7246
   0.750   0.8057   0.00933   0.00356  -0.1788   0.6586   0.7308
   1.000   0.8333   0.00942   0.00363  -0.1790   0.6564   0.7372
   1.250   0.8605   0.00952   0.00373  -0.1790   0.6542   0.7422
   1.500   0.8887   0.00963   0.00383  -0.1793   0.6517   0.7474
   1.750   0.9134   0.00972   0.00391  -0.1789   0.6484   0.7524
   2.000   0.9356   0.00977   0.00400  -0.1779   0.6442   0.7562
   2.250   0.9592   0.00986   0.00410  -0.1772   0.6403   0.7598
   2.500   0.9846   0.00996   0.00420  -0.1769   0.6370   0.7635
   2.750   1.0106   0.01008   0.00430  -0.1767   0.6338   0.7673
   3.000   1.0339   0.01016   0.00443  -0.1760   0.6300   0.7709
   3.250   1.0566   0.01025   0.00456  -0.1752   0.6259   0.7738
   3.500   1.0800   0.01036   0.00469  -0.1745   0.6218   0.7770
   3.750   1.1044   0.01049   0.00481  -0.1740   0.6180   0.7805
   4.000   1.1272   0.01059   0.00497  -0.1732   0.6135   0.7842
   4.250   1.1496   0.01071   0.00512  -0.1724   0.6086   0.7878
   4.500   1.1714   0.01085   0.00527  -0.1714   0.6038   0.7912
   4.750   1.1930   0.01097   0.00546  -0.1703   0.5980   0.7950
   5.000   1.2138   0.01112   0.00564  -0.1692   0.5913   0.7987
   5.250   1.2348   0.01129   0.00583  -0.1681   0.5847   0.8021
   5.500   1.2548   0.01145   0.00604  -0.1668   0.5769   0.8047
   5.750   1.2742   0.01165   0.00627  -0.1654   0.5686   0.8076
   6.000   1.2923   0.01187   0.00652  -0.1637   0.5578   0.8109
   6.250   1.3103   0.01213   0.00680  -0.1621   0.5451   0.8142
   6.500   1.3249   0.01250   0.00713  -0.1599   0.5275   0.8175
   6.750   1.3369   0.01296   0.00754  -0.1572   0.5040   0.8206
   7.000   1.3400   0.01377   0.00820  -0.1529   0.4671   0.8244
   7.250   1.3438   0.01472   0.00897  -0.1490   0.4319   0.8285
   7.500   1.3469   0.01580   0.00986  -0.1451   0.3937   0.8324
   7.750   1.3538   0.01676   0.01070  -0.1420   0.3638   0.8359
   8.000   1.3579   0.01788   0.01168  -0.1385   0.3300   0.8398
   8.250   1.3604   0.01916   0.01279  -0.1349   0.2940   0.8443
   8.500   1.3642   0.02044   0.01391  -0.1317   0.2604   0.8491
   8.750   1.3684   0.02170   0.01504  -0.1286   0.2310   0.8538
   9.000   1.3748   0.02291   0.01616  -0.1259   0.2059   0.8590
   9.250   1.3814   0.02415   0.01732  -0.1233   0.1832   0.8644
   9.500   1.3883   0.02537   0.01848  -0.1209   0.1633   0.8702
   9.750   1.3944   0.02671   0.01977  -0.1184   0.1443   0.8771
  10.000   1.4012   0.02801   0.02103  -0.1161   0.1266   0.8849
  10.500   1.4114   0.03089   0.02384  -0.1113   0.0933   0.9109
  10.750   1.4130   0.03228   0.02524  -0.1084   0.0786   1.0000
  11.000   1.4181   0.03410   0.02699  -0.1065   0.0621   1.0000
  11.250   1.4230   0.03598   0.02880  -0.1047   0.0486   1.0000
  11.500   1.4280   0.03791   0.03069  -0.1031   0.0362   1.0000
  11.750   1.4331   0.03992   0.03266  -0.1016   0.0265   1.0000
  12.000   1.4383   0.04197   0.03469  -0.1002   0.0179   1.0000
  12.250   1.4446   0.04398   0.03670  -0.0990   0.0137   1.0000
  12.500   1.4524   0.04588   0.03865  -0.0980   0.0119   1.0000
  12.750   1.4604   0.04779   0.04062  -0.0971   0.0109   1.0000
  13.000   1.4691   0.04965   0.04256  -0.0963   0.0103   1.0000
  13.250   1.4769   0.05165   0.04463  -0.0955   0.0098   1.0000
  13.500   1.4842   0.05371   0.04676  -0.0947   0.0094   1.0000
  13.750   1.4904   0.05592   0.04904  -0.0939   0.0090   1.0000
  14.000   1.4952   0.05831   0.05152  -0.0932   0.0086   1.0000
  14.250   1.5020   0.06052   0.05381  -0.0926   0.0084   1.0000
  14.500   1.5077   0.06288   0.05627  -0.0920   0.0082   1.0000
  14.750   1.5129   0.06533   0.05881  -0.0915   0.0079   1.0000
  15.000   1.5173   0.06793   0.06150  -0.0911   0.0077   1.0000
  15.250   1.5207   0.07067   0.06433  -0.0907   0.0075   1.0000
  15.500   1.5236   0.07352   0.06727  -0.0904   0.0074   1.0000
  15.750   1.5255   0.07655   0.07042  -0.0902   0.0072   1.0000
  16.000   1.5266   0.07974   0.07370  -0.0901   0.0071   1.0000
  16.250   1.5266   0.08314   0.07720  -0.0901   0.0069   1.0000
  16.500   1.5253   0.08679   0.08095  -0.0902   0.0068   1.0000
  16.750   1.5227   0.09068   0.08494  -0.0905   0.0067   1.0000
  17.000   1.5187   0.09484   0.08921  -0.0909   0.0066   1.0000
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