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EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il)
Reynolds number: 500,000
Max Cl/Cd: 103.4 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ec863914-il-500000.txt
Download as CSV file: xf-ec863914-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EC 86(-3)-914 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4182   0.06302   0.06046  -0.1132   0.9587   0.0236
 -10.000  -0.4523   0.05803   0.05533  -0.1146   0.9543   0.0227
  -9.750  -0.4865   0.05508   0.05227  -0.1119   0.9485   0.0222
  -9.500  -0.4991   0.05235   0.04942  -0.1126   0.9455   0.0226
  -9.250  -0.5231   0.05039   0.04737  -0.1095   0.9393   0.0225
  -9.000  -0.5257   0.04779   0.04462  -0.1102   0.9345   0.0232
  -8.750  -0.4915   0.05070   0.04728  -0.1130   0.9323   0.0272
  -6.750  -0.3202   0.02328   0.01763  -0.1215   0.9178   0.0126
  -6.500  -0.2825   0.02191   0.01612  -0.1241   0.9173   0.0115
  -6.250  -0.2676   0.02122   0.01533  -0.1225   0.9117   0.0112
  -6.000  -0.2327   0.02041   0.01444  -0.1247   0.9100   0.0112
  -5.750  -0.1955   0.01972   0.01367  -0.1272   0.9088   0.0114
  -5.500  -0.1582   0.01921   0.01308  -0.1296   0.9077   0.0116
  -5.250  -0.1204   0.01874   0.01255  -0.1321   0.9068   0.0124
  -5.000  -0.0824   0.01837   0.01209  -0.1343   0.9060   0.0128
  -4.750  -0.0446   0.01809   0.01172  -0.1365   0.9053   0.0128
  -4.500  -0.0065   0.01785   0.01141  -0.1386   0.9046   0.0130
  -4.250   0.0317   0.01764   0.01116  -0.1408   0.9041   0.0133
  -3.750   0.0948   0.01660   0.01070  -0.1441   0.8973   0.1528
  -3.500   0.1300   0.01639   0.01056  -0.1458   0.8954   0.1760
  -3.250   0.1675   0.01614   0.01042  -0.1479   0.8941   0.2061
  -3.000   0.2067   0.01584   0.01024  -0.1504   0.8931   0.2366
  -2.750   0.2474   0.01551   0.01000  -0.1531   0.8923   0.2613
  -2.500   0.2922   0.01499   0.00975  -0.1570   0.8918   0.3210
  -2.250   0.3391   0.01440   0.00945  -0.1615   0.8914   0.4028
  -2.000   0.3896   0.01364   0.00919  -0.1667   0.8912   0.5335
  -1.750   0.4176   0.01347   0.00923  -0.1666   0.8860   0.6068
  -1.500   0.4529   0.01316   0.00893  -0.1676   0.8824   0.6340
  -1.250   0.4926   0.01281   0.00855  -0.1696   0.8807   0.6502
  -1.000   0.5324   0.01242   0.00817  -0.1715   0.8795   0.6606
  -0.750   0.5768   0.01183   0.00756  -0.1743   0.8786   0.6694
  -0.500   0.6214   0.01125   0.00698  -0.1772   0.8779   0.6773
  -0.250   0.6647   0.01083   0.00657  -0.1799   0.8771   0.6838
   0.000   0.6722   0.01097   0.00675  -0.1755   0.8679   0.6887
   0.250   0.7124   0.01060   0.00635  -0.1778   0.8659   0.6949
   0.500   0.7514   0.01024   0.00603  -0.1797   0.8641   0.6984
   0.750   0.7621   0.01032   0.00614  -0.1759   0.8547   0.7020
   1.000   0.8003   0.00996   0.00578  -0.1777   0.8506   0.7071
   1.250   0.8162   0.00999   0.00583  -0.1751   0.8394   0.7110
   1.500   0.8376   0.00995   0.00583  -0.1735   0.8284   0.7137
   1.750   0.8643   0.00984   0.00574  -0.1729   0.8159   0.7179
   2.000   0.8992   0.00965   0.00552  -0.1741   0.7994   0.7242
   2.250   0.9370   0.00940   0.00521  -0.1757   0.7747   0.7275
   2.500   0.9740   0.00942   0.00505  -0.1771   0.7365   0.7307
   2.750   0.9954   0.00980   0.00520  -0.1756   0.6930   0.7349
   3.000   1.0088   0.01030   0.00547  -0.1726   0.6492   0.7398
   3.250   1.0155   0.01088   0.00588  -0.1681   0.6073   0.7435
   3.500   1.0244   0.01150   0.00630  -0.1643   0.5653   0.7478
   3.750   1.0380   0.01210   0.00670  -0.1618   0.5232   0.7515
   4.000   1.0542   0.01268   0.00707  -0.1598   0.4830   0.7534
   4.250   1.0691   0.01323   0.00745  -0.1576   0.4467   0.7546
   4.500   1.0862   0.01375   0.00782  -0.1558   0.4117   0.7558
   4.750   1.1043   0.01429   0.00821  -0.1542   0.3792   0.7569
   5.000   1.1231   0.01481   0.00861  -0.1528   0.3505   0.7582
   5.250   1.1427   0.01532   0.00900  -0.1516   0.3266   0.7597
   5.500   1.1635   0.01579   0.00939  -0.1506   0.3056   0.7611
   5.750   1.1844   0.01628   0.00980  -0.1497   0.2877   0.7624
   6.000   1.2060   0.01675   0.01020  -0.1489   0.2724   0.7637
   6.250   1.2283   0.01720   0.01063  -0.1482   0.2592   0.7650
   6.500   1.2505   0.01765   0.01104  -0.1475   0.2466   0.7664
   6.750   1.2720   0.01812   0.01147  -0.1468   0.2330   0.7678
   7.000   1.2929   0.01856   0.01189  -0.1458   0.2213   0.7689
   7.250   1.3137   0.01902   0.01234  -0.1449   0.2119   0.7699
   7.500   1.3341   0.01950   0.01281  -0.1439   0.2022   0.7710
   7.750   1.3559   0.01991   0.01324  -0.1432   0.1924   0.7722
   8.000   1.3761   0.02043   0.01374  -0.1422   0.1775   0.7734
   8.250   1.3945   0.02111   0.01428  -0.1411   0.1531   0.7747
   8.500   1.4011   0.02284   0.01544  -0.1383   0.0792   0.7759
   8.750   1.3972   0.02565   0.01774  -0.1340   0.0114   0.7772
   9.000   1.4121   0.02675   0.01891  -0.1323   0.0083   0.7788
   9.250   1.4286   0.02769   0.01994  -0.1309   0.0074   0.7803
   9.500   1.4438   0.02876   0.02111  -0.1293   0.0067   0.7815
   9.750   1.4559   0.03003   0.02249  -0.1274   0.0062   0.7826
  10.000   1.4643   0.03161   0.02422  -0.1249   0.0058   0.7837
  10.250   1.4678   0.03358   0.02638  -0.1220   0.0056   0.7848
  10.500   1.4764   0.03512   0.02804  -0.1198   0.0055   0.7860
  10.750   1.4829   0.03684   0.02988  -0.1175   0.0054   0.7872
  11.000   1.4874   0.03877   0.03194  -0.1152   0.0053   0.7885
  11.250   1.4911   0.04084   0.03414  -0.1129   0.0052   0.7898
  11.500   1.4951   0.04294   0.03636  -0.1108   0.0051   0.7913
  11.750   1.4980   0.04521   0.03875  -0.1089   0.0050   0.7929
  12.000   1.5004   0.04765   0.04130  -0.1071   0.0048   0.7944
  12.250   1.5027   0.05018   0.04395  -0.1056   0.0046   0.7959
  12.500   1.5050   0.05274   0.04661  -0.1042   0.0044   0.7971
  12.750   1.5028   0.05592   0.04994  -0.1028   0.0044   0.7982
  13.000   1.5019   0.05910   0.05324  -0.1017   0.0042   0.7995
  13.250   1.4990   0.06268   0.05695  -0.1009   0.0042   0.8007
  13.500   1.4958   0.06645   0.06088  -0.1003   0.0041   0.8020
  13.750   1.4917   0.07050   0.06506  -0.1000   0.0040   0.8033
  14.000   1.4876   0.07473   0.06941  -0.1001   0.0040   0.8047
  14.250   1.4829   0.07922   0.07405  -0.1004   0.0040   0.8060
  14.500   1.4785   0.08378   0.07875  -0.1010   0.0039   0.8073
  14.750   1.4733   0.08855   0.08363  -0.1019   0.0039   0.8086
  15.000   1.4685   0.09343   0.08864  -0.1029   0.0038   0.8098
  15.250   1.4639   0.09832   0.09367  -0.1041   0.0038   0.8109
  15.500   1.4596   0.10323   0.09872  -0.1056   0.0038   0.8121
  15.750   1.4547   0.10826   0.10389  -0.1071   0.0038   0.8132
  16.000   1.4483   0.11344   0.10921  -0.1085   0.0036   0.8142
  16.250   1.4417   0.11883   0.11476  -0.1103   0.0036   0.8153
  16.500   1.4386   0.12397   0.12004  -0.1130   0.0037   0.8171
  16.750   1.4286   0.13013   0.12639  -0.1154   0.0036   0.8182
  17.000   1.4240   0.13568   0.13209  -0.1187   0.0036   0.8200
  17.250   1.4143   0.14221   0.13880  -0.1223   0.0036   0.8215
  17.500   1.4113   0.14769   0.14440  -0.1261   0.0036   0.8235
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